TEST REPORT
EXHAUST EMISSIONS TEST
AIRESEARCH AIRCRAFT PROPULSION
AND AUXILIARY POWER
GAS TURBINE ENGINES
ENVIRONMENTAL PROTECTION AGENCY
OFFICE OF AIR PROGRAMS
GT-8747-R
SEPTEMBER 10, 1971
AIRESEAgCH MANUFACTURING COMPANY OF ARIZONA
- i A DIVISION OF THE GARRETT CORPORATION
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8
.8
TEST REPORT
EXHAUST EMISSIONS TEST
AIRESEARCH AIRCRAFT PROPULSION
AND AUXILIARY POWER
GAS TURBINE ENGINES
GT-8747-R
September 10, 1971
8
8
Prepared by:
Engineering Staff/RCH
a~k~
D. . Boone, Supervisor
Engineering Reports/Data
Group
Approved by:
ta!}» ~~
D. G. Furst,
Chief of Advanced Technology
AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
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REPORT NO. GT-8747-R
TOTAL PAGES
81
ATTACHMENTS:
REV BY APPROVE D DATE PAGES AND/OR PARAGRAPHS AFFECTED
NA RCH See Title 9-10-71 Initial Issue
Page
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AIRESEARCH MANUF"ACTURINr:; COMPANY OF" ARIZONA
A DIVISIDN OF" THE GARRETT CORPDRATION
TABLE OF CONTENTS
Page
1.
INTRODUCTION
1
2.
SUMMARY
3
13
3.
DESCRIPTION OF TEST ENGINE MODELS
4.
DESCRIPTION OF TEST
17
5.
6.
DISCUSSION OF TEST RESULTS
40 to 78
CONCLUSIONS AND RECOMMENDATIONS
79
APPENDICIES:
A - EMISSIONS ANALYZERS AND PRINCIPLES OF
OPERATION (17 pages)
B - EMISSIONS PERFORMANCE DATA REDUCTION
PRINTOUT (33 pages)
C - MEASURED AND CALCULATED EMISSIONS
PERFORMANCE PLOTTED AS A FUNCTION OF
EQUIVALENCE RATIO (75 pages)
D - EXHAUST EMISSIONS STRATIFICATION
CURVES (160 pages)
E - FUEL ANALYSIS AND TYPICAL GAS SAMPLING
ANALYZER TRACES (5 pages)
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Table No.
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11
12
13
1
2
3
4
5
6
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AIRESEARCH MANUf"ACTURING COMPANY Of" ARIZONA
A DIVISION OF THE GARRETT CORPORATION
LIST OF DATA TABLES
Data Description
Engine Exhaust Emissions Over Complete Operating
Load Ran ge
Measured MaxiMin Pollutant Concentrations With
Respect to Power Setting
Application Data Summary of Aircraft Auxiliary
Power and Propulsion Gas Turbine Engines
Gas Turbine Engines Surveyed in Emissions
Measurement Test Program
Maximum Load Limits for Exhaust Emissions
Measurement Test
Engine Power Setting Number Identification
12-Point Movable Versus 12-Point Fixed Sampling
Probe Comparison Test
Comparison of 6-Point Survey (12 and 3 O'Clock)
to 12-Point Survey Average, Using Movable
Sampling Probes
Typical Duty Cycles for Auxiliary Power Units
(APU) On-Board Customer A Commercial Aircraft
Typical Duty Cycles for Auxiliary Power Unit
(APU) On-Board Customer B Commercial Aircraft
Typical Duty Cycles for Turboprop TPE331 Air-
craft Propulsion Engines as Submitted by Light
Twin Engine Airplane Customers D and E
Summary of Estimated APU Duty Cycle Times With
Respect to Commercial Aircraft Service Cycle
Summary of Exhaust Emissions Formation Rate for
Auxiliary Power Units On-Board Commercial
Aircraft
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50
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65
66
67
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION DF' THE GARRETT CORPORATION
Table No.
14
15
16
17
LIST OF DATA TABLES
(Con td)
Data Description
Statistical Emissions Results for AiResearch Gas
Turbine Auxiliary Power Units
Average Emissions Formation Rates for Four
Turboprop (TPE33l/T76) Propulsion Engines
Average Weight of Emissions Generated During
Each Operating Mode of AiResearch Turboprop
(TPE33l/T76) Powered Aircraft .
Statistical Emissions Results for Four
AiResearch Turboprop Propulsion Engines Under
Maximum Shaft Load
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71
74
75
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A OIVISION OF THE GARRETT CORPORATION
LIST OF FIGURES
Figure No.
Figure Description
1
Emission Index for Hydrocarbons as a Function
of Equivalence Ratio for All Engine Series
Tested
2
Emission Index for Carbon Monoxide as a
Function of Equivalence Ratio for All Engine
Series Tested
3
Emission Index for Total Oxides of Nitrogen
as a Function of Equivalence Ratio for All
Engine Series Tested
4
Percent Contribution of NO or N02 in Total
Oxides of Nitrogen (NOx) as a Function of
Equivalence Ratio for All Engine Series
Tested
5
Typical Combustion Systems Used in AiResearch
Engines
6
Emissions Measurement Movable Probe Assembly
7
Control Box for Movable Single-Point Probes
8
Movable Probe Locations as Assigned to a Radial
Clock Position Illustrated on a TPE331 Engine
Test Setup
9
Exhaust Emissions 12-point Fixed Sampling Probe
10
GTC85-90B Exhaust Emissions Measurement by
Fixed Probe Installation
11
Emissions Measurement Test Cart With
Analyzers, Recorders, Calibration Gases and
Sample Probe Assembly
12
Emissions Measurement Test Cart With
Analyzers, Recorders, and Calibration Gases
13
Emissions Measurement Test Cart Analyzers,
Recorders, and Calibration Gases
GT-8747-R
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20
21
22
24
25
26
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION OF' THE GARRETT CORPORATIDN
LIST OF FIGURES
(Contd)
Figure No.
Figure Description
Page
14
Schematic Diagram for Emissions Measurement
Instrumentation on Mobile Cart
30
15
Emissions Sampling Probe Setup Dimensions
for Each Engine Tested
31
16
Emissions Sampling Probe Control Bar Setup
Dimensions Required to Divide Engine
Exhaust Area into Five Equal Annuli
32
17
Exhaust Emissions Measurement Data Sheet
36
18
Emissions Survey Probe Installation Setup
for TPE331 Engine
37
19
Exhaust Emissions Measurement Test Setup
for GTCP660-4
38
20
Exhaust Emissions Measurement Test Setup
for GTC85-90B
39
21
Relationship of Emmission Index for NOx as
N02 and NOx as NO + N02 as a Function of
Equivalence Ratio for the TFE731-2 Engine
Test
46
GT-8747-R
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
/II.. DIVISION OF" THE GARRETT CORPORATION
TEST REPORT
EXHAUST EMISSIONS TEST
AIRESEARCH AIRCRAFT PROPULSION
AND AUXILIARY POWER
GAS TURBINE ENGINES
1.
INTRODUCTION
This report describes the test setup, procedure, and analysis of
exhaust emissions measurements conducted on 32 AiResearch commercial
gas turbine engines comprised of both on-board aircraft auxiliary
power and aircraft propulsion production, overhaul, and development
units. The units selected are currently active in commercial airline
service and thus contribute to aircraft-related pollution levels.
The purpose of this test was to measure exhaust emissions from
auxiliary power and small aircraft propulsion gas turbine engines to
establish base levels of unburned hydrocarbons, carbon monoxide,
carbon dioxide and oxides of nitrogen in current existing engine
designs. In addition, a survey of engine duty cycles as related to
normal customer operation in the field was made to determine a typical
duty cycle and the corresponding estimated level of exhaust emissions
produced.
The emissions test program was accomplished under contract
68-04-0022 with the Environmental Protection Agency, Office of Air
Programs, (formerly the Air Pollution Control Office, APCO).
AiResearch was one of several organizations contracted by the Environ-
mental Protection Agency to conduct gas turbine exhaust emissions'
measurements. Each organization will submit their evaluation of base-
line levels of gas turbine exhaust emissions to assist the Environ-
mental Protection Agency in preparing proposed aircraft emissions
standards.
GT-8747-R
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION OF' THE GARRETT CORPORATION
A special acknowledgement is given to the Environmental Protection
Agency for providing gas analyzer instrumentation, instruction in their
use, and participation in the data accumulation phase of this program.
Measured and calculated exhaust emissions performance is pre-
sented in the following summary of test results.
GT-8747-R
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2 .
SUMMARY
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
It. OIVISION Of" THE GARRETT CORPORATION
2.
SUMMARY
A summary of the exhaust emissions test results for all gas
turbine engines tested are expressed as plots of the respective
emission indexes for total hydrocarbons, carbon monoxide, and total
oxides of nitrogen (expressed as N02) followed by a plot showing the
percent contribution of the constituents NO and N02 in the total
oxides of nitrogen, all as a function of equivalence ratio as shown
in Figures 1, 2, 3, and 4. Emission index is independent of fuel
flow or engine size and is defined as Ib pollutant/1000 Ib of fuel
consumed. Equivalence ratio is defined as the actual fuel-air ratio
at the operating condition to the stoichiometric fuel-air ratio for
the fuel used. In all cases, the band width of the plot includes all
the power settings from the various engine tests and, thus, represents
the total variation in the emission characteristics from each class
of engine tested. The engines were operated from idle conditions
which correspond to the low end of the equivalence ratio scale to the
maximum rated shaft horsepower at the higher equivalence ratios.
Various combinations of bleed-air and shaft horsepower loads were
then applied to the limit of the maximum rated exhaust gas tempera-
tures. The transparent overlays provided represent characteristic
emission indexes for single engine tests on the series engines shown
over a range of power settings for comparison.
Table 1 presents a tabular comparison of all the measured maxi-
mum to minimum emission concentrations for all engine series tested
over the entire operating load range. The emissions results for all
power settings applicable to a given engine are summarized in the.
data reduction printout included as Appendix B. These tabulated data
are represented in plotted form for each engine in Appendix C as
described by the appendix curve index. Section 3. describes each
engine model tested within a given series and further explains the
alpha/numerical code that describes engines at AiResearch.
GT-8747-R
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION OF THE GARRETT CORPORATION
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FIGURE 1
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AIRE5EARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION OF THE GARRETT CORPORATION
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A DIVISION DF THE GARRETT CORPORATION
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION OF THE GARRET CORPORATION
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION OF" THE GARRETT CORPORATION
TABLE 1
ENGINE EXHAUST EMISSIONS OVER COMPLETE. OPERATING LOAD RANGE
Engine Model Series
No. of Engines Tested
Emission
Measured
C02
CO
HC (HOT)
(as methane)
NO
NO
x
(as N02)
NOTE S :
(1)
(2 )
(3 )
(4)
max
min
731 231 331 30 36 85 660 700
1 1 4 1 2 18 2 2
Measured MaxiMin Emission Concentrations in PPM ( 1)
3.03 3.59 3.64 4.07 3.80 4.0 3.45 3.18
2.03 2.46 1.44 1.72 1.52 1.22 1.58 2.28
464.0 345.0 482.0 331. 0 292.0 502.0 (4) 197.0 251.0
24.7 61. 4 13.6 107.0 100. 90.0 77.1 14.8
253.0 99.0 1037.0 52.6 14.6 222.0 28.5 160.0
0.8 7.6 1.3 3.2 0.3 0.3 8.4 18.1
110.0 123.0 120.0 41. 8 54.7 62.0 56.8 109.0
6.2 16.8 1.9 7.7 11.3 1.2 17.0 20.8
116.0 135.0 126 . 0 45.9 61.5 71.2 67.8 114.0
13.9 31.2 11. 0 12.7 18.1 7.7 20.8 33.4
max
min
max
min
max
min
max
min
Emissions data expressed as PPM defined as the volumetric concentration
of pollutant in total wet exhaust products; except C02 is expressed as
mole. percent by volume.
Emissions data measured under Phoenix altitude, ambient temperature and
pressure conditions.
This table does not include GTCP30-92 engine (fuel vaporizer combustion
system) test results.
The maximum CO concentration for the 85 Series engine excluding the
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AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A OIVISION OF THE GARRETT CORPDRATION
The 731, 231, and 85 Series engines produced the highest CO
emissions with a maximum level of 500 ppm from an 85 Series engine.
The 331 Series engines produced the highest hydrocarbon emissions
with the maximum value of 1037 ppm on ground idle, and the 731, 231,
331, and 700 Series engines produced highest NO-NO emissions. The
x
emissions levels of Table 1 are not necessarily representative of the
relative emissions standing of each series when the engines are oper-
ated over their "weighted" duty cycles as discussed and shown in
Section 5. Table 13 shows that when operated under an estimated duty
cycle the 660 Series engine produces the most C02' CO, and NOx emis-
sions and the 700 Series produces the most unburned hydrocarbons in
the auxiliary power unit groups. This is because their duty cycle
time is greater than other engines and in some cases their emission
formation rates are higher than other auxiliary power units. On the
basis of total average weight of emissions per year, Table 13 shows
that the 85 Series engines are the largest contributors because of the
large quantity of engines operating in the field. It was determined
that the 731, 231, and 331 Series engines lose their significance as
large emitters on a duty cycle or total annual emissions comparison
basis. Table 16 shows these values for the turboprop 331 Series
engines.
Table 2 gives a relative comparison of the engines series tested
at idle and maximum load operation. This table essentially defines
the emissions envelope maximum and minimum test values for all product
lines tested at a minimum load condition (flight idle or 100 percent
speed) and a maximum load condition (maximum exhaust gas temperature).
Under low loadings (low equivalence ratios) or high loadings (high
equivalence ratios) the 85 Series engine generated the highest CO and
HC emissions, and the 731, 231, 331, and 700 Series engines created
the highest NO-NO emissions. Lowest emissions of CO and HC occur at
x
maximum load and for NO-NO at idle.
x
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AIRESEARCH MANUFACTURING CCMPANY CF ARIZCNA
A DIVISION 0.. THE GARRETT CORPORATION
TABLE 2
MEASURED MAXIMIN POLLUTANT CONCENTRATIONS WITH
RESPECT TO POWER SETTING
ENGINE MODEL SERIES
731 231 331 30 36 85 660 700
No. Engines Tested 1 1 4 1 2 18 2 2
RANGE OF MEASURED EMISSION CONCENTRATION, PPM(l)
Emission Idle Condition
C02 max 2.20 2.50 1. 86 1.72 1. 63 1. 49 1. 63
min 2.20 2.50 1. 44 1.72 1. 52 1. 22 1. 58 2.32
CO max 264.0 161. 0 248.0 331. 0 146.0 420.0 116.0 78.7
min 264.0 161. 0 125.0 331.0 114.0 125.0 77.1
HC (Hot) max 84.7 21.5 138.0 52.6 14.2 222.0 21.3 58.4
(as methane) min 84.7 21. 5 24.5 52.6 3.5 4.0 11. 2
NO max 14.5 31.0 21.3 7.7 16.0 12.0 18.4 52.6
min 14.5 31.0 6.1 7.7 11. 3 1.2 17.0
NO max 21.1 42.5 42.0 12.7 21. 3 21. 4 23.5 64.3
x min 21.1 42.5 20.0 12.7 18.1 7.7 20.8
(as N02)
Full Load
C02 max 3.03 3.59 3.64 4.0 3.80 3.94 3.32 3.10
min 3.03 3.59 3.40 4.0 3.79 3.16 3.30 3.06
CO max 24.7 61. 4 38.9 112.0 243.0 298.0 177.0 22.1
min 24.7 61.4 13.6 112.0 117.0 109.0 143.0 20.4
HC (Hot) max 0.8 7.6 5.9 3.8 3.9 73.3 15.0 69.6
(as methane) min 0.8 7.6 1.3 3.8 0.4 1.1 10.0 28.8
NO max 110.0 123.0 120.0 39.2 47.5 60.1 53.9 90.8
min 110.0 123.0 62.0 39.2 47.4 30.2 46.5 76.1
NO max 116.0 135.0 126.0 42.7 59.7 66.4 64.8 94.3
x min 116.0 i35. 0 66.5 42.7 54.7 38.8 55.0 79.7
(as N02)
NOTES: .
1. Emission concentration measured in parts per million, ppm, by volume except C02 as
mole percent.
2.
Idle operation given for propulsion engines is flight idle condition or power setting
2. For APUs idle represents 100 percent speed power setting 1 except for the 700-4
idle represents 91 percent speed "standby mode" of power setting 2.
3.
.Fu11 load operation for propulsion engines is represented by power setting 20 and for
combination load APUs as power setting 15.
4.
Power setting numbers represent reference engine load conditions as defined in
Table 6.
5.
These data summarize the measured emissions performance data reduction printout
enclosed as Appendix B of this report.
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A. DIVISIDN OF' THE GARRETT CORPORATION
All engines produced higher levels of N02 emissions than were
suspected to exist in either gas turbine exhaust emissions as
reported in other industry surveys or from chemical kinetics formation
reactions. Figure 4 shows the highest N02 levels occurring at idle
with N02 comprising one-fourth to three-fourths of the total oxides of
nitrogen generated. A check of several data points using a non-
dispersive ultra-violet (NDUV) analyzer was made to confirm the mag-
nitude of N02 readings on the chemiluminescent analyzer. The effect
of water vapor in the exhaust gas on the reading level of the chemi-
luminescent analyzer was also checked by an ice bath condenser,
described in Section 5., and found to agree closely with calculated
values. It is important to realize that the total oxides of nitrogen
as NO + N02 emitted from gas turbines appears considerably higher if
expressed as N02 rather than NO + N02. The effect of an expression
using the N02 molecular weight is shown by Figure 21 to be about
50 percent greater than the actual emission of NO + N02 from the
TFE731-2. This practice as requested by the Office of Air Programs
intends to allow for the photoreactivity of NO in the atmosphere with
conversion to N02 in 3 to 5 hours.
The statistical approach to catagorizing engine families is shown
in Tables 14 and 17. Statistical definition of upper emissions levels
that would include ~ high proportion of an existing gas turbine popu-
lation is not considered practical. This is because emissions levels
of identically designed production gas turbines vary by such large
amounts that a statistical upper control limit to include a high per-
centage of an existing population becomes unreasonably high.
Three sampling probe measuring techniques were used to obtain gas
samples during this program. The single point fixed probe is the
easiest to use but cannot be accepted as reliable due to significant
radial and circumferential emissions stratification as discussed in
Section 5. The 12 point fixed probe is next easiest to use but when
compared to a single point movable probe small differences in readings
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION Dr THE GARRETT CCRPD~ATIDN
resulted as shown in Table 7, Section 5. Additional sampling should
be conducted with this probe on engines with large exhaust emissions
stratifications to substantiate the validity of its averaging ability.
The single point movable probe is considered the most accurate mea-
suring method and was used on all engines measured in this program.
Although smoke measurements were not taken in this report, the
single point movable probe was designed and used according to SAE
Recommended Practice ARP-1179. A trend to include smoke measurements
in emissions tests would suggest that emissions measurement procedures
adopt the probing technique of ARP-1179 or a change be made to the
smoke measuring practice to reflect the emissions measuring probing
technique preferred.
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TEST ENG
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION Of" THE GARRETT CORPORATION
3.
DESCRIPTION OF TEST ENGINES
The emissions measurement test program conducted at AiResearch
Manufacturing Company of Arizona under the Environmental Protection
Agency involved tests on a total of 32 auxiliary power and prime pro-
pulsion gas turbine engines designed for business/executive aircraft
and military and commercial airline transport aircraft. Table 3 shows
a list of the gas turbine engine 'models tested, present application,
and the maximum rated performance for the application shown. Basi-
cally 15 different engine models comprise the 32 gas turbines tested.
The basic number shown denotes a given engine model series all
members of which have basically the same power section configuration.
The dash number reflects a particular engine model different from the
other engines in the same series by combinations of the performance
rating definition, a growth version, application, or change in exter-
nal configuration required for a given installation. Finally, the
preceding letter code describes the gas turbine's basic function.
For example, GTCP means a gas turbine compressor unit with shaft
power capabilities and TSCP means twin~spool compressor and shaft
power unit, while TPE, TSE, and TFE denot~s turboprop, turboshaft,
and turbofan engines respectively.
The functions of an auxiliary power unit (APU) are to provide
combinations of shaft power (for generators and other accessories) and
bleed-air for aircraft engine starting, aircraft air conditioning,
anti-ice, and heating systems.
The 36, 85, 660, and 331 Series gas turbines are single-shaft
engines that operate at essentially constant speed over the range of
load conditions. The 700 and 731 Series are twin-spool engines that
operate at variable low pressure spool speeds. Of particular sig-
nificance from the standpoint of the emission study are the variation
in cycle characteristics and the difference in the combustion systems
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AI RESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION Dr THE GARRETT CQRPORA,TlON
TABLE 3
APPLICATION DATA SUMMARY OF AIRCRAFT
AUXILIARY POWER AND PROPULSION UNITS
Engine Model
Application
Small APUs
GTCP30-92
GTCP36-6
Executive Jets
Grumman Gu1fstream II
'0(;)
III 1-3
1.01
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Commercial Aircraft APUs
GTCP85-98
GTCP85-98CK
GTCP85-180 (98CK)
GTCP85-98D
GTCP85-115
GTCP85-129
GTC85-90/90B
GTCP660-4
TSCP700-4
Boeing 727-100 3 720 100 108
Boeing 272-100, -200 6 325 100 128
Military (substitute for 98CK) 325 177 158
McDonnell-Douglas DC-9 2 790 94 67
BAC 1-11/400, 500 3 325 40 110
Boeing 737 1 335 200 110
Air Ground Cart 3 940 0 124
Boeing 747 2 225 63 493
McDonnell-Douglas DC-10 2 15 142 385
Propulsion Enqines
TPE33l-201A/151G
TPE331-3U-303G
TPE331-43A
T76-G-410
TSE231-l
Skyvan, CASA (212)
Swearingen (Merlin IrC)
Aero Commander (NAR)
Military (substitute for 201A)
Development Unit for Lear
(Gates) and Bell
Helicopter
Development Unit for
Dassault Falcon 10,
Lear Jet 26, and
Swearingen SA28T
TFE731-2
Total
MAXIMUM RATED PERFORMANCE*
(SEA LEVEL, STATIC, U.S. STANDARD
DAY EXCEPT AS NOTED)
Number Engines Shaft Bleed Air Inlet Temp
Engines Delivered Load Extraction Other Than
Tested Thru May' 71 shp 1b/min 59°F
2 230 40 28.5 113
2 140 30 53
100
100
103
100
100
103
2 321 715,665
o 60 840
1 86 575
1 820 720
1 0 474
THRUST, LB
1 2 3500
-
32
* Performance Ratings Shown are less than or equal to Engine Power Settings used in the
Emissions Measurement Test Program. Maximum loads shown may not be simultaneously possible in all cases.
Total Military and Commercial Auxiliary Power Units Delivered Through May 1971 = 21,745 Approx.
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AIRESEARCH MANUF'ACTURING COMPANY OF' ARI~ONA
A DIVISION OF' THE GARRETT CORPDRATION
of the basic engine series. The three basic types of combustion
systems used in the gas turbine for this emission study are shown in
Figure 5.
A basic description of each engine series tested plus a cross-
section view of each are included in the following engine series
information cards provided by the AiResearch Sales Department.
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AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
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SERIES
30
The "30" series Gas Turbine is the smallest of the AiResearch engines. Various
models of this engine produce shaft power in a range from 60 to 150 H.P. and
weigh approximately 75 pounds.
AIRESEARCH
GAS TURBINE ENGINES
The "30" engine is a compact and rugged source of constant speed shaft power
for driving generators, alternators, pumps, compressors and other driven equip-
ment. Most installations require only shaft horsepower, however, some models
of this engine can provide a continuous supply of bleed air in combination with
shaft power. Some typical applications of the "30" are: business aircraft
auxiliary power units, generator sets for ground power and pump drives.
-------
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30
SERIES
The "30" series Gas Turbine Engine is the simple,
open-cycle coupled-turbine type, consisting of
compressor. combustor, turbine assembly, output shaft
and accessory drive. In addition. the unit incorporates
fuel. lubrication, and control systems. All components
are assembled into a single unit.
The compressor is a single-stage centrifugal type
utilizing an open-faced, backward-curved impeller. Air
flows through a screen inlet, is compressed in the
impeller and diffused in a radial, vaned diffuser, dis-
chc:rging into the outer plenum surrounding the nozzle
and turbine torus assembly. The impeller is mounted
on a common shaft with the turbine rotating assembly
and the accessory assembly. The shaft is supported by
two high-speed bearings.
The power turbine section consists of a turbine
assembly, a plenum and a torus. and a combustor
chamber assembly. The plenum serves as a receiver for
the compressor discharge air and as an enclosure for
the combustion flame tube and the torus. The torus,
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IGNITOR
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TURBINE
mating with the discharge end of the combustor
chamber flame tube, directs the hot combustion gases
through a fixed area nozzle ring against the turbine
wheel.
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The accessory section with integral drive pad and
output shaft includes the following: an oil pump
assembly including pressure pump, oil filter, by-pass
and relief valves; a fuel accessory assembly which
includes fuel pump. fuel filter. relief and by-pass valves.
governor and fuel shutoff valve. Unit speed is regulated
by a governor in the fuel pump and control unit
assembly.
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The engine contains controls suitable for completely
automatic starting. These controls properly sequence
starter operation. fuel control. and ignition to provide
a stable automatic starting cycle requiring only the
engagement of a single starter switch. Additional con-
trols provide continuous operating adjustments to
compensate for variations in shaft power requirements,
and ambient conditions.
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For detail information on the specific gas turbine engine for your
requirements call your nearest Garrett Corporation Office. or send
your problem statement directly to:
GAS TURBINE SALES
AIRESEARCH MANUFACTURING COMPANY OF ARIZONA, 402 South 36th Street, Phoenix, Arizona 85034
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SERIES
36
The "36" series gas turbine is one of the latest designs to join the AiResearch
family of engines.
It will supply about 70 pounds of bleed air per minute. approximately 200 shaft
horsepower, or, varying combinations of both at the same time. This engine
weighs approximately 140 pounds.
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A/RESEARCH
GAS TURBINE ENGINES
The "36" series gas turbine is a compact and rugged source of pressurized
and heated air in addition to shaft power. The pneumatic energy is used in a
variety of applications for jet engine starting systems. air conditioning systems.
anti-ice and heating systems. The shaft power output is used for driving gener-
ators. alternators. pumps. compressors and other driven equipment. Typical
applications of the "36" are: ground power utility packages providing electrical
power and air conditioning services, airborne auxiliary power units
and generator sets.
-------
36 SERIES
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The major components of the "36" series Gas Turbine
Compressor and Power Unit include a single-stage
single-entry centrifugal compressor. a single can-type
combustor, a single-stage radial-inflow turbine. acces-
sory section with an integral output pad. and the
controls and accessories necessary for automatic start-
ing and governed-speed operation of the engine. The
compressor and turbine rotating elements are mounted
on a single shaft supported by two bearings.
Air enters the inlet screen and plenum and is compressed
by the backward-curved centrifugal impeller and radial
diffuser system. The compressed air is discharged into
the annular plenum where a controlled portion of it
can be bled off for external use. The remaining air is
directed' into the reverse-flow single-can combustor.
Fuel is added through a single nozzle and the tempera-
ture of the burned mixture is raised to the value required
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for the particular engine load. From the combustor, the
hot gas is directed by the scroll and fixed-area nozzle
through the turbine wheel to produce the power required
for driving the compressor. accessories. and the
output load.
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The accessory section provides drives for the oil
pressure pump. oil scavenge pump. fuel control and
starter motor in addition to the output pad for the
generator or other major driven equipment.
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The "36" series engine includes controls for completely
automatic starting and operation. They sequence starter
operation, fuel control and ignition to provide a stable
starting cycle requiring only the engagement of a sin&le
starter switch. They also provide continuous control to
compensate for variations in power requirements and
ambient conditions.
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For detail information on the specific gas turbine engine for your
requirements call your nearest Garrett Corporation Office. or send
your problem statement directly to:
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GAS TURBINE SALES
AIRESEARCH MANUFACTURING COMPANY OF ARIZONA, 402 South 36th Street, Phoenix, Arizona 85034
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SERIES
85
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The "85" Series Gas Turbine has the largest production history and variety of
applications of the AiResearch engines. Models of this engine develop power
in the 200 to.350 equivalent H.P. range and weigh approximately 275 pounds.
Most applications utilize this power in a combination of varying amounts of
shaft power and compressed air energy. .
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AIRESEARCH
GAS TURBINE ENGINES
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The "85" engine is a compact and rugged source of pressurized and heated air.
This pneumatic energy is used in a variety of applications for jet engine starting
systems, air conditioning systems, anti-ice and heating systems. A few installa-
tions require only this pneumatic power but many models of the "85" also
provide shaft power at the same time. This shaft power is used for driving
generators, alternators, pumps, compressors and other driven equipment.
Typical applications of the "85" are: airline and military transport aircraft
auxiliary power units and generator sets for ground power.
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85
SERIES
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The basic "85" series gas turbine includes a compressor,
turbine, and an accessory section with controls.
The compressor section is designed to provide a source
of compressed air for the turbine and for external
pneumatic power. The compressor is a two-stage
centrifugal type utilizing two radial outward flow
impellers. Air enters the double entry first stage impeller
through a compressor inlet plenum. flows through a
vaned diffuser into crossover ducts leading into the
inlet of the single entry second stage. Air discharges
from the second stage compressor through a vaned
diffuser into the turbine plenum.
The turbine section consists of a turbine assembly,
pneumatic bleed port and control. plenum and torus,
and a combustor chamber assembly. The plenum serves
as a receiver for the compressor discharge air and as
an enclosure for the combustion chamber and the torus.
The torus, mating with the discharge end of the com-
bustor chamber flame tube, directs the hot combustion
gasses through a fixed-area nozzle ring against the
turbine wheel. The main rotating assembly is mounted
on pressure lubricated bearings.
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FUEL NOZZLE
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FIRST STAGE COMPRESSOR
SECOND STAGE COMPRESSOR
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BLEED AIR CONTROL VALVE
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The accessory section includes: An oil pump assembly
including pressure pump and dual scavenge pump,
oil filter, by-pass valve, and relief valve; a fuel accessory
assembly which includes fuel pump, fuel filter, relief
and by-pass valves, governor, and fuel shutoff solenoid;
a centrifugal three-speed switch, starter motor and a
cooling fan. Fan air capacity is sufficient for cooling
lubricating oil. and for cooling driven equipment. The
lubricating oil is passed through an oil-to-air heat
exchanger which is mounted on the unit. Action of the
- fuel governing system depends upon a functional rela-
tionship between load and governed speed for adequate
stability. The accessory section includes an integral
drive pad and output shaft where shaft horsepower is
required in combination with bleed air power.
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The "85" is equipped with a fully automatic control
system which properly sequences starter operation,
fuel control, and ignition to provide a stable automatic
starting cycle requiring only the engagement of a single
starter switch. Additional automatic controls provide
continuous operating adjustments to compensate for
variations in compressor bleed load, shaft power
requirements and ambient conditions.
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For detail information on the specific gas turbine engine for your
requirements call your nearest Garrett Corporation Office. or send
your problem statement directly to:
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GAS TURBINE SALES
AIRESEARCH MANUFACTURING COMPANY OF ARIZONA, 402 South 36th Street, Phoenix, Arizona 85034
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SERIES 660
The "660" series gas turbine is the largest engine of its kind available.
Approximately 300 shaft horsepower. 700 pounds per minute bleed air. or
varying combinations of both at the same time are available from this 560 pound
engine.
AIRESEARCH
GAS TURBINE ENGINES
-----'
The "660" engine is one of the latest developments in large airborne auxiliary
power units. This rugged engine produces very large quantities of heated and
pressurized air to be used in aircraft engine starting systems. air-conditioning
systems, anti-ice and heating systems. The "660" also provides the shaft power
required for driving generators, alternators. pumps. compressors and other
driven equipment. Experience gained from the world leadership of AiResearch
in development. production and support of gas turbine engines guarantees the
future of the "660" as an efficient and dependable engine. New models of these
engines will be able to take full advantage of the growth capability of the basic
design. Typical applications of the "660" are: large transport aircraft onboard
auxiliary power units and as ground power equipment.
-------
660 SERIES
The basic "660" series gas turbine includes a
compressor. turbine and accessory section with
controls.
The compressor section is designed to provide the
compressed air required for engine operation. as well
as the large quantity that is taken as pneumatic power
for external use. Air from the inlet plenum enters the
four-stage axial compressor. The compressed air is then
diffused to a lower velocity as it is directed into the
turbine plenum where a controlled quantity can be
bled for external use. The rest of the compressed air
enters the annular combustor where fuel is added and
the temperature of the burned mixture is raised to the
value necessary to meet load requirements. The hot
gas from the combustor is then directed through the
first and second stage axial turbines where the power
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TURBINE PLENUM
SURGE CONTROL VALVE
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TWO STAGE TURBINE
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IGNITOR
FUEL NOZZLE
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FOUR STAGE COMPREssOR
SECOND STAGE SURGE
CONTROL VALVE
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ACCESSORY SECTION
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is extracted to drive the compressor, accessories and
shaft power output. The main rotating shaft is mounted
on two bearings.
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The accessory section includes an integral output pad
for driven equipment as well as the necessary electrical
fuel and oil system components. These include an oil
cooler that is mounted on the engine. The "660" is
equipped with a fully automatic control system that
properly sequences starter operation. fuel control. igni-
tion. and surge control to provide a stable. automatic
starting cycle requiring only the engagement of a single
starter switch.
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Additional automatic controls provide continuous
operating adjustments to compensate for variations in
bleed air load. shaft power requirements and ambient
conditions.
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For detail InfDrmation on the specific gas turbine engine for your
requirements call your nearest Garrett Corporation Office. or send
your problem statement directly to:
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GAS TURBINE SALES
AI RESEARCH MANUFACTURING DIVISION OF ARIZONA, 402 South 36th Street, Phoenix, Arizona 85034
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SERIES 7 0 0
The "700" series gas turbine is a Twin-Spool Compressor and Power engine
(TSCP) that weighs approximately 550 pounds. It provides over 150 shaft
horsepower along with approximately 350 lbs/min of compressed air energy
and has been designed for easy maintenance and long life.
AIRESEARCH
GAS TURBINE ENGINES
The series "700" gas turbine is an advanced-technology engine that provides
the most favorable fuel consumption characteristics possible with the current
state of the art, coupled with the excellent maintainability required for airline
APU operation. This optimized cycle is accomplished with a twin-spool, coaxial,
high-pres sure-ratio cycle with shaft power extraction from the constant speed
high-pressure spool and bleed air from the low-pressure spool. Variable
nozzles are provided at the first-stage turbine of the low-pressure spool to
control the pneumatic output to satisfy the load requirements and thus minimize
the fuel consumption.
Typical applications of the ''700'' include the new large commercial transport
aircraft where this advanced APU furnishes the pneumatic power for air-
conditioning systems, main engine starting, and the shaft power for the auxiliary
electrical and hydraulic systems.
-------
~
700 SERIES
LOW PRESSURE COMPRESSOR
BLEED AI R DUCT
FUEL NOZZLE
HIGH PRESSURE COMPRESSOR
COMBUSTOR
HIGH PRESSURE TURBINE
LOW PRESSURE TURBINE
VARIABLE TURBINE NOZZLE
DIFFUSER
IGNITOR
TOWER SHAFT
ACCESSORY SECTION
OUTPUT SHAFT
low-pressure spool that limits bleed air output to the
level required to satisfy the selected operating
conditions.
The "700" series gas turbine is a two-spool engine with
the high-pressure spool operating at a constant speed
and the low-pressure spool operating over a controlled
speed range.
The high-pressure spool has a single stage radial
compressor driven by a single stage axial flow turbine.
The output power of the high-pressure spool is trans-
mitted to the gearbox to provide constant speed shaft
power for the engine accessories and the customer
furnished driven equipment.
Air from the inlet duct is compressed by the low-
pressure compressor and flows to the inlet of the
high-pressure compressor. The output of the high-
pressure compressor is diffused and directed through
the annular combustor where it picks up the heat
energy from the burning fuel/air mixture. The high-
energy gases are directed through the high-pressure
turbine and finally through the two-stage turbine of
the low-pressure spool.
The three-stage, axial-flow, compressor of the low-
pressure spool is driven by a two-stage axial-flow
turbine. Bleed air is extracted from the engine through
ports located between the last stage of the low-pressure
compressor and the inlet to the high-pressure com-
pressor. The variable flow feature of the low-pressure
turbine nozzle permits control of the energy delivered
to that turbine and the resulting speed control of the
The "700" series engine is equipped with a fully
automatic control system that sequences starter. fuel
control. ignition and all other functions to assure a
stable automatic starting cycle as well as maintaining
control over all operating conditions.
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For detail information on the specific gas turbine engine for your
requirements call your nearest Garrett Corporation Office. or send
your problem statement directly to:
III
GAS TURBINE SALES
AI RESEARCH MANUFACTURING DIVISION OF ARIZONA, 402 South 36th Street, Phoenix, Arizona 85034
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AIRCRAFT ENGINES TURBOSHAFT
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ACCESSORIES
AIR INLET
POWER TURBINE
IGNITOR PLUG
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FUEL NOZZLE
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COMBUSTOR GAS
2 STAGE COMPRESSOR GENERATOR
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REDUCTION GEARS
POWER OUTPUT SHAFT
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GARRETT/AI RESEARCH
AIRCRAFT ENGINES TURBOPROP
-------
IPE 331
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PROPellER SHAFT
2 STAGE CENTRIFUGAL COMPRESSOR
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3 STAGE AXIAL TURBINE
IGNITOR PLUG
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FUel NOZZlE
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COMBUSTOR
INTEGRAL INLET DUCT
REDUCTION GEARS
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GARRETT/AI RESEARCH
AIRCRAFT ENGINES T U R B 0 FAN
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AIR INTAKE
FAN
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FAN REDUCTION GEARBOX
LOW PRESSURE COMPRESSOR
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HIGH PRESSURE COMPRESSOR
HIGH PRESSURE TURBINE
IGNITOR PLUG
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LOW PRESSURE TURBINE
FUEL NOZZLE
. COMBUSTOR
ACCESSORY DRIVE POWER TAKEOFF SHAFT
ANGLE DRIVE GEARBOX
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1),1:; ::;C.I{ 1 P'l' 1 UN
OF TE ST
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISIDN OF' THE GARRETT CORPORATION
4.
DESCRIPTION OF TEST
The gas turbine exhaust emissions measurement tests were con-
ducted at the AiResearch, Phoenix, test laboratories during the months
of April, May, and June 1971. Thirty-two AiResearch commercial gas
turbine engines were tested. These include 26 auxiliary power and 6
aircraft propulsion gas turbine engines. Table 4 lists the specific
engine models tested in chronological order together with the aviation
turbine fuels used, number of power settings or load conditions, and
the number of probe locations from which gas ~amples were extracted
at the exit plane of the engine tailpipe.
On several occasions a particular engine model was not available
from production, development or overhaul for a scheduled test. An
engine substitution was possible by obtaining for test the equivalent
military engine counterpart. Each unit belongs to the same engine
series and therefore have identical power section components and cycle
characteristics. Usually, only the performance rating and/or the
external configuration is the primary difference between these engines.
Thus it was possible to substitute the GTCP85-l80 military engine for
the GTCP85-98CK commercial engine simply by operating at a lower engine
speed. Similarly, the T76 military engine was substituted for the
TPE33l-201A turboprop engine.
The tests were conducted in accordance with the test procedure
contained in GT-87l3-R except as noted in subsequent paragraphs.
Emission measurements were performed on the engines at essentially
sea level, static operating conditions. Prevailing engine inlet air
temperatures ranged from 700F to 11ooF, with an average relative
humidity of 16 percent. Special test equipment was required in
addition to the test equipment and instrumentation normally used for
engine acceptance tests: A description of the special test equipment
is as follows:
GT-8747-R
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AIRE5EARCH MANUFACTURING COMPANY OF ARIZONA
A DIVlalON 0" nn: DARRETT CORPORATION
Engine Model
1.
2.
3.
4.
5.
GTCP85-129
TPE331-1-151G
GTCP85-98D
GTCP85-90B
T-76-G-410
6.
7.
GTCP85-98D
TPE331-43A
8.
9.
10.
GTCP85-115
GTCP36-6
GTCP36-6
11.
12.
13.
GTCP85-98
GTCP30-92
GTCP30-92
(Vaporizer)
GTCP85-98
GTCP85-90
GTCP85-98
TSCP700-4
GTCP660-4
GTCP660-4
TSCP700-4
TPE331-1-151G
GTCP85-98CK
GTCP85-115
TFE731-2
14.
15.
16.
17.
18.
19.
20.
21.
22.
23.
24.
25.
26.
27.
28.
GTCP85-115
GTCP85-180
GTCP85-180
GTCP85-180
(98CK)
GTCP85-180
( 9 8CK )
GTCP85-180
(98CK)
GTCP85-90B
29.
30.
31.
32.
TSE231-1
Abbreviation Key:
TABLE 4
, .,
GAS TURBINE ENGINES SURVEYED IN EMISSIONS MEASUREMENT
TEST PROGRAM
Test unit
From
0/8
P
0/8
P
0/8
0/8
0/8
0/8
0/8
0/8
0/8
0/8
0/8
0/8
0/8
0/8
P
P
0/8
P
0/8
0/8
0/8
D
0/8
P
P
P
P
P
0/8
D
Serial No.
P-34763
P-91168
P-27692
P-24504
G.E. 00790
(P for 2 weeks)
P-27857
P-61157
P-18725
P-34772
P-34696
P-15454
P-28794
P-28794
P-15257
P-5786
P-15541
P-90122
P-37705
P-37596
P-90123
P-91165
P-35648
P-18781
7305
P-18702
P-567
P-507
P-518
P-595
P-593
P-24376
2301
Test
Date
4-29
5-1
5-3
5-5
5-6
5-7
5-11
5-13
5-14
5-14
5-17
5-17
5-18
5-18
5-19
5-21
5-24
5-25
5-26
5-27
6-1
6-7
6-8
6-10
6-11
6-14
6-14
6-15
6-15
6-16
6-16
6-18
Fuel
JP-5
JP-5
JP-5
JP-4
JP-5
JP-5
JP-4
JP-5
JP-5
JP-5
JP-5
Av kero
Av kero
Av kero
Av kero
Av kero
Av kero
JP-5
JP-5
JP-5
JP-5
Av kero
Av kero
Av kero
Av kero
Av kero
Av kero
Av kero
Av kero
Av kero
Av kero
JP-5
Av kero
No. of
. Power
Settings
10
6
10
6
6
10
2
6
10
8
6
(Plus
10
10
10
10
5
10
12
10
11
12
6
10
10
6
(Smoke
10
10
10
10
10
11
(NOx ice bath
5
(12 point
6
No. of Probe
Locations
10
10
10
10
10
10
10
10
10
10
10
bleed-air)
10
10
10
10
20
10
10
10
10
10
10
10
10
10
samples)
10
10
10
10
10
10
test)
12
probe)
10
0/8 = Overhaul, P = Production, D = Development, Av kero = Aviation
kerosene (jet A)
GT-8747-R
-------
~
AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A DIVISION OF' THE GARRETT CORPORATION
Sample Probe Assembly, SKP26000 - Figures 6 and 7 shows
the sample probe assembly and its control box which permitted
the operator to actuate the probes from a remote area. The
assembly is comprised of two adjustable single point probes,
one to survey the vertical and the other to survey the hori-
zontal radii of the engine tailpipe. Each are mounted on the
same support stand, SKP26093, shown in Figure 6. Each probe
could be translated by a drive motor to each of five positions
along a given radii in the engine exhaust exit plane 90 deg
apart and may be reversed to pickup an additional 10 gas
samples. Figure 8 shows the movable probe locations as
assigned to a radial clock position, illustrated on a TPE331
engine test setup. Each probe was center-positioned in each
of five equal annulus areas. Since each engine series has
different tailpipe areas, a control bar for each was designed
with machined slots corresponding to the precise probe location
desired within each of 5 equal annulus areas determined for
each engine tailpipe area. An appropriate control bar was
then attached to each sample probe and mated to the drive
train of the probe actuator motor. Probe advance was con-
trolled by a microswitch that followed the control bar between
machined slots in the bar, thereby providing an electrical
I
step input for each successive advance once energized by the
remote control box. A position indicator was mounted on each
probe to indicate the probe position at any time. A three-way
solenoid actuated valve joining the horizontal and vertical
sample gas lines was automatically thrown each time either the
horizontal or vertical drive motor was energized thereby per-.
mitting only gas sample flow from the desired probe to reach
the gas analyzer instrumentation on the test cart at a given
time.
GT-8747-R
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISICN OF' THE GARRETT CORPDRATION
'PROBE POSITIONING
MOTOR
7
VERTICAL SAMPLE PROBE'
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(PROBE LOCATIONS' 6-10 AND,,f6-20)'
"INSULATED SAMPLE LINE
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THERMOSTAT!
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PROBE
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EMISSIONS MEASUREMENT MOVABLE
PROBE ASSEMBLY
Figure 6
MP-31080
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MOVABLE PROBE LOCATIONS AS ASSIGNED
TO A RADIAL CLOCK POSITION ILLUSTRATED ON
A TPE331 ENGINE TEST SETUP
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FIGURE 8
GT-8747-R
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION OF" THE GARRETT CORPORATION
A 24 volt dc power supply available from the test cell was
required to actuate the probe drive motors. Also, a 110 volt ac
power supply was wired to the probe sup~ort stand to energize
the electrical strip heaters wrapped around the gas sample lines
to minimize adsorption/desorption of hydrocarbon molecules in
the sample lines. Similarly, the 10 foot gas sample line made
from 3/16 in. inside diameter, stainless steel tubing, leading
to the instrumentation test cart was heated to a temperature of
approximately 310°F to minimize the same physical property hydro-
carbons exhibit of adhering to the walls of the sample line.
All engines were tested using the movable probe, while
several turbine emissions measurement programs conducted out-
side of AiResearch were using a fixed probe approach to
emissions measurement. Consequently, AiResearch designed a
similar fixed probe to compare test results obtained using both
the movable and fixed probe measuring techniques on the same
engine. The design was made specifically for the 85 Series
engines and incorporates 3 sampling points ,in each of 4 branches
which are manifolded to a single sample line as shown in
Figures 9 and 10. Each sample collection point lies centered
within equal annulus tailpipe areas. Figure 10 shows the probe
mounted to a GTC85-90B gas turbine using a standard Marman clamp.
Twelve-point movable versus 12-point fixed (average) and 6-point
movable versus 12-point movable sample data were collected on
this engine. Comparisons of the resultant emissions measurements
were made and are included in the following section of discussion
of test results.
Portable gaseous emissions measurement instrumentation as
provided by the Office of Air Programs, Environmental Protection
Agency are shown mounted on an AiResearch designed mobile test
cart in Figures 11, 12, and 13. All gas analyzer instruments,
GT-8747-R
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AIRESEARCH MANUF'ACTURING COMPANY OF' ARIZONA
A DIVIBION 0" THE GARRETT CDRflOAATtDH
85 SERIES ENGINE
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INSIDE OF FITTING TO
INSIDE OF PROBE TUBES
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MATERIAL :
347 STAINLESS STEEL
NOTE:
1.
PROBE DIAMETER, 2R, SIZED SO THAT IT CAN BE HELD TO TAILPIPE BY A MARMAN
CLAMP (SEE DETAIL "A").
EXHAUST EMISSIONS 12-POINT FIXED
SAMPLING PROBE ASSEMBLY
FIGURE 9
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MP-30091
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RECORDERS
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Figure 11
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Figure 13
GT-8747-R
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION OF' THE GARRETT CORPORATIDN
tanks of calibration gases, vacuum pumps, recorders, and
servicing tools are installed on the test cart. Figure 14 shows
a schematic diagram of the final integrated system as setup for
continuous on-line gas sampling and automatic recording of
emissions measurements. Exhaust gaseous emissions were measured
by the following instrumentation. Two nondispersive infrared
analyzers (NDIR) were used for the measurement of carbon dioxide
and carbon monoxide. A heated flame ionization detector (FID)
measured the emission of total unburned hydrocarbons. The
nitric oxide emissions were measured by a chemiluminescent
analyzer (CNOA), and a thermal converter was employed to convert
. the nitrogen dioxide to nitric oxide so that the concentration
of total oxides of nitrogen was also indicated. A technical
description of each gas analyzer instrument is included as
Appendix A of this report.
With the background information regarding special test equipment
provided above, attention will be directed toward describing the
general test procedure applied to each engine. Each unit was installed
in a normal acceptance test configuration. The movable sampling probe
assembly was then setup as instructed in Figures 15 and 16. The
engine was started and loaded over a range of power settings or load
conditions consistent with the application duty cycle for that engine.
For example, a typical load range was from idle (no-load, governed
speed) to maximum shaft load at zero bleed or from idle to maximum
bleed air extraction and zero shaft load. Also, combined bleed/shaft
loads were run on several engines. Maximum load limits for this test
program are shown in Table 5 followed by the estimated limiting
exhaust gas temperature, EGT as shown in Table 6 for each mode
of operation. Once steady-state operation was achieved at a given
load condition, the exhaust emissions were sampled by the movable
sampling probe apparatus and measured by the gas analyzer instrumen-
tation in the manner previously described. Exhaust emissions were
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HORIZONTAL PROBE
LOCATIONS
9
ENGINE SERIES
30
36
85, 95
831
165
700
660
T76, 331
731
231
SETUP
DIMENSION - X
0.13
0.16
0.21
0.23
0.19
0.26
0.34
0.24
0.28
0.18
6
NOTES:
1. SAMPLING PROBE ASSEMBLY SKP26000 INSTALLED AT EXIT PLANE OF ENGINE TAILPIPE.
2. HORIZONTAL AND VERTICAL PROBE SETUP DIMENSIONS FOR EACH ENGINE SERIES TESTED ARE
LISTED AS SHOWN AND ARE LOCATED FROM THE INSIDE DIAMETER OF THE OUTER TAILPIPE
WALL. THIS INITIAL SETUP POSITION ALONG WITH USING THE APPROPRIATE PROBE CONTROL
BAR SETUP ACCORDING TO FIGURE 16 WILL CENTER POSITION THE SAMPLING PROBE WITHIN
EACH OF THE FIVE EQuAL ANNULUS AREAS THAT COMPRISE THE ENGINE TAILPIPE AREA.
3. DOTS REPRESENT FIVE POSSIBLE SAMPLING PROBE POSITIONS AT 3, 6, 9 and 12 O'CLOCK
LOCATIONS FACING THE ENGINE TAILPIPE.
EMISSIONS SAMPLING PROBE SETUP DIMENSIONS
FOR EACH ENGINE TESTED
FIGURE 15
G'l'-8747-R
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AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A DIVISION or THE GARRETT CORPDRATION
PART NO. A B1 B2 B3 B4 L
SKP26009-1 GTCP30 .27- .29 .59- .61 .99-1.01 1.60-1.62 5.97-6.03
-2 GTCP36 .33- .35 .73- .75 1.23-1.25 1.95-1.97 5.97-6.03
-3 GTCP85 .43- .45 .95- .97 1.59-1.61 2.51-2.53 5.97-6.03
-4 GTPR831 .49- .51 1.05-1.07 1.69-1. 71 2.49-2.51 5.97-6.03
-5 GTCP165 .38- .40 .81- .83 1. 29-1. 31 1. 85-1. 87 5.97-6.03
-6 TSCP700 .96- .98 2.08-2.10 3.45-3.47 5.45-5.47 6.62-6.68
-7 GTCP660 1.00-1.02 2.16-2.18 3.60-3.62 5.69-5.71 6.62-6.68
-8 TSE231 .37- .39 .80- .82 1. 28-1. 30 1. 84-1. 86 5.97-6.03
-9 T76 .53- .55 1.15-1.17 1.91-1.93 3.01-3.03 5.97-6.03
-10 TFE731 .61- .63 1. 32-1. 34 2.20-2.22 3.47-3.49 5.97-6.03
REFERENCE POSITION FOR
FOLLOWER CAM
B4
B3
B2
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~L(TAB)
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EMISSIONS SAMPLING PROBE CONTROL BAR
SETUP DIMENSIONS REQUIRED TO DIVIDE ENGINE EXHAUST
AREA INTO FIVE EQUAL ANNULI
FIGURE 16
GT-8747-R
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TABLE 5
MAXIMUM LOAD LIMITS FOR EXHAUST EMISSIONS MEASUREMENT TEST
Engine Model
Engine
Rotor Speed
Percent
Shaft
Load
shp
Bleed Air
Extraction
lb/min
Max Rated
EGT, of
(combination
Shaft/Bleed)
Auxiliary Power Units
l.
2.
GTCP30-92
100
40
28.5
1320
GTCP36-6
10C
100
160
160
68.5
1200
3.
GTCP85-98
(-98D, -115)
128
1250
4.
GTCP85-98CK
100
160
128
1150
5.
6.
GTCP85-l29
GTCP85-l80
(sub for -98CK)
100
100
160
110
1200
160
158
1200
7.
GTC85-90
(-90B)
100
o
122
1175
8.
GTCP660-4
100
300
275
1215
o
515
LP-Spool
Speed, Nl
j
60
(Idle)
80
142
Max available
(Limited by max EGT)
!
1005
9.
TSCP700-4
142
1005
99
142
142
1005
1005
100
AIRCRAFT PROPULSION ENGINES
(SEA LEVEL, STATIC, STANDARD DAY)
10. TPE33l-43A 65 No --
(Idle) Load
100 575 --
11. TPE33l-l51G 65 No --
(Idle) Load
100 665 --
12. TPE331-201A 65 No --
(Idle) Load
100 715 --
13. T76-G-4l0 65 No --
(sub for -201A) (Idle) Load
100 715 --
14. TPE331-3U-303G 65 No --
(Idle) Load
100 840 --
1060
1060
1060
1060
1060
1060
Maximum
Inter-Turbine
Temperature
15.
TSE23l-l
65
(Idle)
100
No
Load
--
474
--
1404
Maximum
Thrust. Ib
16.
TFE731-2
100
3500
--
1545
NOTES:
1. Engine tests were run at Phoenix (altitude = 1092 ft) and at prevailing ambient
temperature, pressure, and humidity.
2. Maximum shaft/bleed loads shown are not simultaneously possible when maximum EGT is
limiting.
3. Shaft load limits shown does not necessarily reflect the maximum shaft load capability
specified in the application rating.
4.
See Table 6 for the corresponding engine power setting reference numbers that identify
engine load condition.
GT-8747-R
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISIDN OF" THE GARRETT CORPORATIQN
TABLE 6
ENGINE POWER SETTING REFERENCE NUMBERS
CORRESPONDING TO LOAD CONDITIONS
Shaft or Combined
Thrust Load Shaft or Bleed Air Extraction Bleed/Shaft Load
shp or lb Thrust Only % Maximum Bleed
% Maximum Load 1 u lJ"~ or Max Rated
(Table 5) Only 25 50 75 EGT, of
o 1 2 3 4 5
25 6 10
50 11 15
75 16 19
100 20 22
ESTIMATED EXHAUST ~S TEMPERATURE. LIMITS
FOR
EMISSIONS TEST
Power Setting
Number
(EGT)test equals --
1
EGT specified for ground idle condition
2
Propulsion engines:
EGT specified for flight idle
Auxiliary power units:
(EGT) . dl + 1/4 [(EGT) - (EGT). dl ]
~ e max ~ e
3 (EGT) idle + 1/2 [(EGT) - (EGT) idle]
max
4 (EGT)idle + 3/4 [(EGT) - (EGT) idle]
max
5 (EGT) shown in Table 5
max
GT-8747-R
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AIRESEARCH MANUFACTURING CCMPANY CF ARIZCNA
iii. DIVISION 0" THE GARRETT CORPORATION
continuously monitored on strip chart pen recorders. Example strip
chart recordings are included in Appendix E of this report. Also, at
each test condition, pertinent engine performance data was recorded
on data sheet$ similar to that shown in Figure 17. Figures 18, 19,
and 20 show photographs of example test setups for three gas turbine
engines. Appendix B contains the emissions performance data reduction
printout which shows a tabulation of the engine performance data ob-
tained ~or each engine at each power setting comprising the load run
schedule for the emissions measurement tests. Also tabulated are
measured emission concentration in ppm, calculated emission index,
lb/1000 lb of fuel consumed, and the calculated emission formation
rate in lb/hr for each power setting and constituent emission. The
following section will describe how each emission performance param-
eter is calculated.
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ENGINE MODEL , SiN , DATE FUEL:
ENGINE LOAD LIMITS (TABLE ): SHP , EGT of ENGINE: PRODUCTION
BAROMETER: IN. Hg A OVERHAUL
BEFORE RUNNING TEST, CALL 273-7511 FOR DEWPOINT: of
RELATIVE BDMITITY: " DEVELOPMENT
DATA POINT
SPEED, N" RPM
COMPR INLET TEMP of
FUEL FLOW OBSERVED LB/BR
TORQUE. IN.-LB
EGT. of
INLET VENTURI N!, IN. H20
C"C"M'PR nT!':C"R ""...,,., TIII- Rrr
BLEED CONDITIONS
BLEED ORIFICE PRESSURE IN.Ra
BLEED ORIFICE TEMP of
BLEED ORIFICE AP IN. H2O
ORIFICE DIMENSION: ALTITUDE IQUI..E.' DIYISIOII
CALc.uta. EXHAUST GAS EMISSIONS DATA B16156
SPEED FACTOR: RrCORDID APeO PROGRAM
ROTAMETER NO.: oa&.. WIS 517 /71 FIGURE 17
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5.0
DISCUSSION OF TEST RESULTS
The preceding section described the test procedure and equipment
used to collect and measure exhaust gaseous emissions on 32 commercial
gas turbine engines. This section will begin by informing the reader
of the various analytical criteria used to evaluate the following:
( a)
Data reduction calculations
(b)
Curve presentation of resultant emissions performance
(c)
Sampling probe measurement techniques
After providing this background information emissions measurement
test results will be discussed. Then, emission test results will be
evaluated on the basis of an estimated engine duty cycle as determined
for each aircraft engine application.
As was previously described, 10 emissions sample single-point
movable probe readings were obtained for nearly all engines at each
power setting. A mean value of the 10 readings was obtained and a maxi-
mum deviation (T-sigma) from this mean was determined. A statistical
distribution test was applied to the 10 sample readings to determine
whether or not the sample fits a two-sided or "bell" distribution. If
it did, probe readings were eliminated with the statistical assurance
that 99 percent of the eliminated data was questionable. If a reading
was eliminated by this test, a new mean value was determined from the
remaining probe readings and the distribution test was reiterated.. The
concluding mean value of the probe readings are then used in all tabu-
lar, including data reduction computer printout and curve plots pre-
sented in this report. The emissions performance data reduction print-
out and measured and calculated emissions performance plotted as a
function of equivalent ratio are included in Appendices Band C
GT-8747-R
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A. DIVISION OF' THE GARRETT CORPORATION
respectively of this report. Other analytical criteria established
for emissions performance in the data reduction calculations are as
follows.
Fuel-Air Ratio
During planning phases of this program it became obvious that
inlet air flow or exhaust gas flow measurement would be impractical.
A T76 propulsion engine was operated with an inlet flow measuring
bellmouth and emissions data was recorded with the APCO equipment.
Fuel-air ratios calculated with the use of emissions data were found
to be within 5 percent of those determined from measured air and fuel
flows. Accordingly, the use of fuel-air ratio as computed from exhaust
emission measurement and fuel composition was recommended for the
purpose of emissions programs in preference to fuel-air ratio deter-
minations based on airflows obtained from measured or from estimated
engine performance.
In the reduction of the data from the APCO equipment, the carbon
monoxide and carbon dioxide recordings were considered as dry analysis
data because of the use of a'desiccant in the sampling train. The
recordings of total hydrocarbons and oxides or nitrogen, however,
include the water vapor initially in the air plus the water vapor
formed by the combustion process. Accordingly, the concentrations of
total hydrocarbons and oxides of nitrogen were corrected ,initially to
dry conditions as follows:
8"
8 =
I-v-w
GT-8747-R
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AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A DIVISION OF" THE GARRETT CORPCRATIDN
Where:
8 - volumetric concentration of pollutant species
(eitre r CH4' NO or NOx) in dry exhaust gas.
8" -
volumetric concentration of pollutant species in wet
exhaust gas containing water vapor in prevailing ambient
air plus water vapor fonned by combustion process
v - mole fraction of water vapor in
ambient conditions of air = h Me
M
w
w - mole fraction of water vapor formed from combustion
exhaust from initial
process
R
= '2 (a + b + d)-2D
h - lb water vapor/lb dry air at engine inlet
M - molecular weight of exhaust products = 29.0 lb/ lb/-mole
e
M - molecular weight of water vapor = 18.02 lb/lb-mole
w
a - mole fraction of carbon dioxide in dry exhaust
b - mole fraction of carbon monoxide in dry exhaust
d - mole fraction of total hydrocarbons (expressed as CH4) i~
dry exhaust. Use d" in Equation (1)
R - hydrogen/carbon ratio of atoms in fuel
GT-8747-R
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AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A. DIVISION 0" THE GARRETT CORPORATION
For presentation of the test results on a volumetric basis, the
most useful form of emission data appears to be in terms of percent
(or ppm) by volume of wet exhaust gas from a combustion process with
dry air. Accordingly, the dry volumetric concentrations of the
emissions were corrected by the relationship:
8' = 8(1-w)
Where
8' - volumetric concentration of pollutant species in wet
exhaust gas containing only the water vapor formed by
the combustion process.
From the chemical equation of the combustion process, the fuel-
air ratio can be determined from the expression:
(MC + ~)
f = ~
(a + b + d)
[ 1 + ~R + ~. (~ - 1) + d. (~ - 2) ]
(3 )
where terms not previously defined are:
f - fuel-air weight ratio, 1b fue1/1b dry air
~ - molecular weight of air = 28.9 1b/1b-mole
M - atomic weight of carbon - 12.01 lb/lb-atom
c
~ - atomic weight of hydrogen = 1.008 1b/1b-atom
Emissions Index
An emission index expressed as pounds of pollutant per pound of
fuel consumed was calculated from the equation
GT-8747-R
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION Dr THE GARRETT CORPDRATION
S'M
s
ES = (MC + RMH) (a' + b' + d')
(4 )
where prime values indicate wet measurements and terms not previously
defined are:
E - emission index, lb pollutant species, S/lb of fuel
S
consumed
MS - molecu1a+ weight of pollutant species S, 1b/lb-mo1e
= 44.01 for C02
= 28.01 for CO
= 16. 04 for CH 4
= 30.01 for NO
= 46.01 for N02
Note that the total oxides of nitrogen on an emission index basis
could be computed as N02 only or the sum of ENO + ENO where the volu-
2
metric concentration of N02 must be determined from the difference of
the NO - NO readings. A comparison of total oxides of nitrogen were
x
calculated by these two methods for the TPE73l-2:
(a)
Considering all oxides of nitrogen as N02
(b)
Considering total oxide flow as the sum of NO flow and N02
flow
GT-8747-R
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION DF' THE GARRETT CORPORATION
The difference in emission index and pollutant flow rate for the
two methods is substantial as shown by Figure 21. At the peak thrust
condition measured, the flow calculated using Method 1 is 49-percent
higher than that calculated using Method 2. The first method is
predicated upon the atmospheric conversion of NO to N02 within 3 to 5
hours from the time of combustion. For this program, at the request
of OAP (APCO), all emissions were computed on the basis to total
oxides of nitrogen expressed as N02'
Formation Rate
The formation rate of emissions for use in computing the total
weight of emissions fbr a particular engine load cycle can be deter-
mined from
FS = ES x Wf
Where FS - formation rate of pollutant species S, lb/hr
Wf - engine fuel weight-flow rate, lb/hr
Volumetric concentration, emissions index, and
rate for each engine tested together with the engine
are presented on test summary printout in Appendix B
emission formation
performance data
of this report.
Several methods were examined before selecting the most adequate
method of plotting emissions performance data. Emissions data are
known to vary as a function of such engine parameters as shaft load
. . . '. . . . .. - ".' ~ ..
and bleed load, combustor parameters including combustor inlet airflow,
pressure, temperature (including combustor discharge temperature
referred to standard day conditions), fuel-air ratio and equivalence
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PI 8
lQl
CD 00
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d'\-...J
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~
AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
0.5
r-I
0.4
N
o
z
+
o
Z 0.3
U)
..:t:
x
o
Z
H
~ 0.2
..........
N
o
Z
U)
..:t:
X .
o 0.1
Z
H
~
o
0.14
" OIVI8.QN Dr THE. Q"'..CTT CO....OItATION
0.17 0.18 0.19
~, EQUIVALENCE RATIO
RELATIONSHIP OF EMISSION INDEX FOR NO
X
AS N02 AND NOX AS NO+N02 AS A
FUNCTION OF EQUIVALENCE RATIO
FOR THE TFE731-2 ENGINE TEST
0.15
0.16
SI . 46.01
N
EINO AS NO 12.01 + b + d)
EINO AS NO + = EINO + EINO
2
SNO (30. 1) + SN02(46.01)
[12.01 + (1.008)]( + b + d)
0.20
O~21
0.22
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION Of" THE GARRETT CORPORATION
ratio. Since shaft load and bleed load are not conveniently related
as a single parameter for emissions plots, and since both loading
methods affect combustor fuel-air ratio or equivalence ratio, the most
suitable choice for data correlation appeared to be one of these com-
bustor parameters. As a test for determining which parameter would
better represent the independent variable or abscissa for emissions
plots, two curves were plotted and compared with respect to data
scatter using 85 Series engine data. The data used for comparison is
shown on Pages 50 and 53 of Appendix C. It was concluded that the
difference between data points observed in each plotted band or envelope
of emissions were negligible regardless of the abscissa chosen.
Using equivalence ratio as the independent variable has the fol-
lowing advantages:
.
(a)
Equivalence ratio is defined as the actual fuel-air ratio at
the operating condition to the stoichiometric fuel-air ratio
for the fuel used. Consequently, a direct comparison of
emissions results may be made regardless of the fuel used.
(b)
Both shaft and bleed-air extraction load engine performance
data can appear on the same curve.
Therefore, all emissions performance data and pertinent engine perform-
ance data were plotted as a function of equivalence ratio and appear in
Appendix C of this report. Also note that Appendix C data was broken
down into engine groups in accordance with field service applications
and as coincidently related to aircraft size. Accordingly,
Group I - Propulsion Engines - TPE331- TFE731, TSE231 and
T76 Engine models
Group 2 - Small Auxiliary Power Units - GTCP30 and GTCP36 Engine
Series used on-board small business/executive aircraft
Group 3 - Medium Size Auxiliary Power Units - GTCP85 Engine Series
used on-board Boeing 727 and 737, BACI-II or DC-9 Aircraft
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AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A DIVISION Of'" THE GARRETT CDRPORATION
Group 4 -
Large Auxiliary Power Units
Engine Series used on-board
Aircraft
- GTCP660 and TSCP700
Boeing 747 and DC-IO
Furthermore, note that because of the large quantity of data
accumulated, data points of individual engine tests are not shown
connected. Engine groups were surrounded by envelopes or bands to
identify possible trends in the data. If a group consisted of only
one or two engines, the maximum data of the sample size tested was
shown by a single line.
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
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Emissions Samplinq Probe Measurement Techniques
Of the three methods for obtaining exhaust gaseous emissions
from gas turbine engines in use at the present time the single-point
movable sampling probe technique as used in this test program is con-
sidered to be the most accurate. Unfortunately, it is also the most
cumbersome to use. Improved accuracy over the sample readings taken
by the single-point fixed probe and 12-point fixed probe as described
earlier in the description of test Section 4. may be attributed to
the aerodynamic cleanliness of the movable sampling probe design and
the movable feature which permits sampling sometimes significant
variations in emissions radial and circumferential to the engine
tailpipe.
Table 7 presents 12-point movable (average of 3, 6, 9 and 12
o'clock positions) emissions measurements compared to the 12-point
average fixed probe measurements for test conducted on GTC85-90B, a
"bleed" engine, over a range of power settings. Although the emission
measurement differences can be significant when the working range of
the given gas analyzer instrument is small, no conclusions were deter-
mined because of the limited number of engines tested.
Further investigation was made regarding emissions results ob-
tained from, the movable probe assembly. Table 8 presents a comparison
of a 6-point survey, 3 readings each, at the 12 and 3 o'clock position
to a 12-point surveyor 3 readings in each of the 12, 3, 6 and 9
o'clock positions covering the entire tailpipe. It was concluded
that the majority of the data taken in this test program along th~
radii (5 readings each) leading to the 12 and 3 o'clock positions is
a good representation of the data taken at all four radial locations.
A comparison of Tables 7 to 8 shows that the data obtained by the
6-point survey, at the 12 and 3 o'clock positions, more closely repre-
sents the l2-point survey, at the 12, 3, 6, and 9 o'clock positions,
than the l2-point averaging probe.
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AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
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12-POINT MOVABLE VS 12-POINT FIXED SAMPLING PROBE COMPARISON TEST
TABLE 7
Samplinq Probe Used
Movable
6-point survey,
6-point survey,
(12 & 3 0' clock)
(6 & 9 o'clock)
Average
Fixed
Difference
[l-(fixed/movable, avg)] 100, %
Movable
6-point survey, (12 & 3 o'clock)
6-point survey, (6 & 9 o'clock)
Average
Fixed
Difference
[l-(fixed/movable, avg)] 100, %
Movable
6-point survey, (12 & 3 o'clock)
6-point survey, (6 & 9 o'clock)
Average
Fixed
Difference
[l-(fixed/movable, avg)] 100, %
Movable
survey, (12 & 3 o'clock)
survey, (6, & 9 b' clock)
Average
Fixed
Difference
[l-(fixed/movable, avg)] 100, %
6-point
6-point
Movable
6-point survey, (12 & 3 o'clock)
6-point survey, (6 & 9 o'clock)
Average
Fixed
Difference
[l-(fixed/movable, avg)] 100, %
NOTES:
1. Probe
2. Power
3. Fixed
.!
Emissions Measurement at the Power Setting Reference No. Shown
£
1
4
5
1.49
1.49
1.49
1.47
0.02
1.3
387
404
395
390
5.0
-1.25
16.4
17.9
17.15
16.5
0.65
:t3.3
8.3
13.5
10.9
10.5
0.4
4.0
C02 Mole %
1. 97
1.94
1. 955
1.93
0.025
1.3
2.44
2.45
2.445
2.43
o . 0 15
0.06
3.02
3.08
3.05
2.95
0.10
3.3
3.50
3.57
3.535
3.49
0.045
1.3
470
467
468.5
471
2.5
-1
CO, PPM
,507
399
395
397
419
22.0
5.5
452
462
457
465
8.0
1.8
513
510
501
9.0
-1.8
NOx' PPM
23.7
23.0
23.35
22.3
0.05
5
36.4
36.4
36.4
35.0
1.4
4.0
43.1
43.1
43.1
40.0
3.1
7.75
28.9
29.4
29.15
28.0
1.15
4.3
12.6
17.6
15.1
17.5
2.4
-13.7
NO, PPM
17.1
33.7
39.5
36.6
31.0
4.6
16.2
35.9
33.9
34.9
25.0
9.9
40.0
25.1
21.1
18.0
3.1
17.2
HC (Hot) , PPM (Propane)
7.5 3.7 1.5 0.2 0.15
0.9 5.1 2.8 0.6 0.26
4.2 4.4 2.15 0.4 0.205
1.0 0.6 4.2 1.8 1.85
3.2 3.8 2.0 1.4 1.6
Not a representative test range, ppm too'low for comparison
comparison test conducted on GTC85-90B, SiN P-24376, June 16, 1971
setting number definitions 1 through 5 shown in Table 6.
probe comprised of 12 gas sample collection points'manifolded to a single sample line.
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AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A DIVIBION Of' THE BARRETT CORPORATION
TABLE 8
COMPARISON OF 6-POINT SURVEY (12 AND 3 O'CLOCK) TO 12-POINT
SURVEY AVERAGE, USING MOVABLE SAMPLING PROBES
Samp1inq Probe Used
Movable
6-point survey, (12 & 3 o'clock)
6-point survey, (6 & 9 o'c1ock)
12-point average
Difference
[1-(6 pt/12 pt average)] 100, %
Movable
6-point survey, (12 & 3 o'clock)
6-point survey, (6 & 9 o'clock)
12-point average
Difference
[1-(6 pt/12 pt average)] 100, %
Movable
6-point survey, (12&3. o'clock)
6-point survey, (6 & 9 o'clock)
l2-point average
Difference
[1-(6 pt/12 pt average)] 100, %
Movable
6-point survey, (12 & 3 o'c1ock)
6-point survey, (6 & 9 o'clock)
12-point average
Difference
[1-(6 pt/12 pt average)] 100, %
Movable
6-point survey, (12 & 3 o'clock)
6-point survey, (6 & 9 o'clock)
12-point average
Difference
[1-(6 pt/12 pt average)] 100, %
NOTES:
1.
2.
Emissions Measurement at the Power Setting Reference No. Shown
1.
1
i
1
C02 Mole %
!
1.49
1.49
1.49
o
o
1.97
1.94
1.955
0.015
0.8
2.44
2.45
2.445
0.005
0.2
3.02
3.08
3.05
0.003
0.1
3.50
3.57
3.535
0.035
1.0
CO, PPM
387 470 507 452 399
404 467 513 462 395
395 468 . 5 510 457 397
9.0 1.5 3.0 5.0 2.0
2.3 0.3 0.6 1.1 0.5
NOX' PPM
16.4
17.9
17.15
0.75
4.4
23.7
23.0
23.35
0.35
1.5
28.9
29.4
29.15
0.25
0.9
36.4
36.4
36.4
o
o
43.1
43.1
43.1
o
o
8.3
13.5
10.9
2.6
2.4
NO, PPM
17.1
25.1
21.1
4.0
1.9
33.7
39.5
36.6
2.9
8.0
35.9
33.9
34.9
1.0
0.3
12.6
17.6
15.1
2.5
1.7
He (Hot), PPM (Propane)
7.5 3.7 1.5 0.2. 0.15
0.9 5.1 2.8 0.6 0.26
4.2 4.4 2.15 0.4 0.205
3.3 0.7 0.65 0.2 0.055
78.5 16.0 30.2 50.0 26.8
Probe comparison test conducted on GTC85-90B, SiN P-24376, June 16, 1971
Power setting number definitions 1 through 5 shown in Table 6
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AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
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With these facts in mind a brief review of the significant
features to the emissions stratification data presented in Appendix D
will be made.
(b)
(c)
(d)
For example:
(a)
GTCP85-180, SiN P-567 - C02' NO, and NOx readings for bleed
air test conditions at probe No.1 are grouped lower than
other probe readings. (Note that probe numbers or locations
are identified in Figure 8.) This possibly represents an
example of ambient-air recirculation at probe location No.1
with correspondingly lower readings expected for CO and
HC (Hot) .
Radial emissions stratification is shown by probe locations
1 to 5 or 6 to 10~ circumferential stratification is shown
by comparing probes locations 1 to 5 with probe locations 6
to 10.
In order for a 12-point fixed probe such as shown in Figure
9 to represent single-point movable probe data plotted in
these curves, the fixed probe at locations 1, 3, 5, on the
curves must be representative of data obtained by the movable
probe at locations 1, 2, 3, 4, 5~ probe locations 6, 8, 10,
must be representative of data obtained at probe locations
6, 7, 8, 9, 10, and so on.
Examples of data showing a significant lack of agreement
with the criteria of statement (c) above are itemized below:
~ Figure
Enqine Test No. Emission No.
GTCP36-6 P-34772 5, 10 CO 5-81
GTCP85-98 P-15454 5, 22 CO '5:"'126
GTCP85-98 P-15257 5, 10, 15, 19, 22 CO 5-131
GTCP85-115 P-18725 10, 22 CO 5-141
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
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(e)
Examples of data with significant stratification in the
circumferential location change of 3 o'clock to 12 o'clock
are itemized below:
Enqine EilL Test No. Emission Fiqure No.
TPE33l-l-l51G P-9ll65 1 HCH 5-47
TPE33l-l-l51G P-9ll68 1 HCH 5-53
TPE33l-43A P-6ll57 1 CO, HCH 5-56/57
GTCP30-92 P-28794 5,10,15, CO, NO, 5-66/68/69
(Atomizers) 19,22 NO
x
GTCP660-4 P-37596/ All HCH, NO 5-177/179
37705 x
TSCP700-4 P-90l22/ All C02, HCH 5-186/187/
90123 NOx 188
(f) Emissions symbols plotted as zero ppm represent probe loca-
tion data eliminated from the samples by means of the
-.. - -.. . . .
"Student's T" distribution te~t previously discussed in this
section or probe locations that were intentionally omitted.
(g)
On two GTC85-90/90B engines, SIN P-5786 and P-24376, 20 probe
locations as defined in Figure 8 are plotted instead of ten.
It is realized that the gas turbine industry does have a
a standardized emissions measurement technique and a need for
regarding the reliability of data obtained for each technique
need for
knowledge
studied.
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
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Evaluation of Test Results
Emissions performance test results with respect to measured
levels of constituent emissions for each engine, from one engine to
another, and for extremes of power setting may best be discussed by
reviewing the tabular summary of Appendices Band C shown in Tables 1
and 2. These tables are shown in the Summary Section 2. Also,
observe Figures 1, 2, 3, and 4 in the Summary. Each figure shows the
basic trends in emission performance exhibited by each engine series
tested on the basis of emission index plotted as a function of equiv-
alence ratio and how they compare to one another. These curves
reflect essentially the same trends observed for measured levels of
emissions concentration about to be discussed.
Table 1 presents the
extremes observed for measured emission concentrations in parts per
million, ppm, for each engine series tested over the complete operating
load range. Also, the number of engines tested is included to reflect
the fact. that as the number of engines tested in a given series
increases so does the measured minimum to maximum emissions levels.
The GTCP30-92 engine tests using a vaporizer combustion system
were not included in the table so as not to influence the 30 Series
engines comparative value to other engines in the table. The 30 and
85 Series engines produced highest C02 emissions; the 731, 331, and 85
Series engines produced highest CO emissions; the 331 Series engine
produced highest hydrocarbon emissions, and the 731, 231, 331, and 700
Series engines produced highest NO - NO emissions. However, it must
x. .
be realized that this is not necessarily representative of the relative
emissions standing of the engine series when the engines are operated
under the weighted duty cycles discussed in subsequent paragraphs.'
Table 2 gives a relative comparison of these engines at idle and
full load operating conditions. For the idle operation correlation
the propulsion engine data is presented for the increased flight idle
speed to compare to APU idle operation at 100 percent speed. The
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
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700 APU at 100 percent speed is always loaded. Therefore, a value of
91 percent speed (standby operation) with no shaft loading was chosen
for the comparison. Full load for propulsion engines is represented
by test power setting 20 and for APU's by power setting 15 as defined
in Table 6. This table essentially defines the envelope maximums and
minimums for all AiResearch product lines tested at a minimum load
condition (flight idle) and a maximum load condition (maximum exhaust
gas temperature in typical application).
The trends in the propulsion engine group show the effects of
three different engine configurations. These configurations are:
first, a fixed shaft speed TPEi second, a variable speed two-spool
TFE731 enginei and third a gas generator free-turbine 231. All three
engine configurations operated over the cycle-pressure ratio range of
2.5 to 6.0, but showed different slopes of emission versus equivalence
ratio. The difference in slopes is attributed to the fact that the
variable speed engines can to a large extent, adjust combustor airflow
to meet loading changes or fuel flow changes. In contrast, the fixed
shaft speed engines are relatively inflexible with respect to adjust-
ment of airflow. A large change in loading or fuel flow results in
but a small change in airflow for these engines. The result is a
narrower equivalence ratio band for variable speed engines.
This trend is also obvious if the fixed shaft TPE is raised in
speed from the ground idle or 65 percent maximum speed to the governed,
flight idle, 100 percent speed. The slope that would result by con-
necting the two idle data points would be very steep and cover a
narrow equivalence ratio. Although the fuel-air ratio effect dis-.
cussed here is noticeable, it should be noted that other parameters
such as combustor inlet pressure, temperature rise, mixing, etc., are
also involved to a lesser degree.
Comparison of the 36 Series engine emissions with 30 Series emis-
sions reveals that the can-type combustor of the 30 Series yield a
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
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lower level of emissions than the 36 Series of the same basic size.
The difference could be attributed to the small sample size or the
combustor design but would require further investigation before any
degree of certainty could be applied.
Vaporizing and atomizing type combustors were tested on a 30
Series engine. However, the sample size tested was again too small
to draw definite conclusions in view of the data scatter observed in
other engine tests. However, on the basis of a single comparative
test, the vaporizer emitted less hydrocarbons and more oxides of
nitrogen than the atomizing combustor. Carbon monoxide emissions
were lower for the vaporizing combustor on the low load only.
A sample group of three GTC85-90/90B (bleed-air extraction only)
engines were singled out of the 85 Series family because of their
inherently higher CO emission level. This engine has a smaller com-
bustor than any other 85 Series engine which probably accounts in-
directly for the high CO emission by a mixing geometry influence on
the combustion process. Other emissions for the GTC85-90j90B were
within the envelopes defined by other 85 Series engines.
In the case of the fifteen combination load-type 85 Series
engines, it was of interest to note that the GTCP85-98, SiN P-1554l,
appeared at the top of the 85 Series hydrocarbon envelope, while the
GTCP85-98, SiN P-11527, of the same series type, appeared near the
bottom of this envelope. At the high equivalence ratios, this com-
parison of two engines indicated hydrocarbon content ranging from 1.0
ppm to 100 ppm (see Appendix C, page 44).
The data spread observed in comparing these 85 Series engines
can most likely be attributed to the wide variety of combustor designs
used in the 85 Series engines; however, the hydrocarbons comparison
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above is a good example of the emissions distribution difference from
one engine sample to another. In general, the following hardware dif-
ferences exist in this engine group.
(a)
The GTCP85-98, -98D, -115, and -129 engine models use the
same radial-flow compressors, atomizers, and turbine wheels,
but different flame tubes and turbine nozzles.
(b)
The GTCP85-98CK and -180 engine models use the same radial-
flow compressors, flame tubes, atomizers, and turbine
wheels, but use different turbine nozzles.
The 660 engines showed a CO emission curve that was almost flat
with increasing load. This characteristic would have to be studied
further before an explanation could be presented; however, the
straight-through flow annular combustor is a design configuration not
used in engines other than the 660 Series and may be partially respon-
sible for the flat co characteristic. This engine also has a high
compressor surge bleed on low loads which requires higher turbine
temperatures during a low through flow condition. Operation under
this surge bleed condition contributes to the flat CO characteristic
by producing CO at idle more comparable to CO at high loads. Surge
bleed air from the compressor is dumped into the turbine exhaust and
contributes somewhat to the HC reading instabilities at low loads.
Engines in the 700-4 group also have variable speed capabilities,
steep slope emissions curves, and the narrow equivalence ratio band
indicated by the 731/231 propulsion engines. Emission levels were
also more comparable to the propulsion engines group rather than the
other APU groups.
If a comparison between annular and can-type combustors is
desired, an overlay of Group 1 or Group 4 curves (which show the
effects of using existing annular burner configurations) upon Group 2
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
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or Group 3 curves, (which show the results of engines using existing
can-type burner configurations) can be made. With high loading or
high equivalence ratios, the annular burner configurations give a
lower CO and HCH emission level, but higher NO emission levels.
x
These differences in emission levels could logically be attributed to
the higher combustion temperatures employed in annular burner designs
and geometric differences between the two types of burners, atomizers
and mixing methods. However, investigation of atomizing and mixing
geometries could provide considerable areas for future work and would
result in a better understanding of these differences.
All engines produced higher levels of N02 emissions than were
suspected from other industry surveys. Highest levels of N02 occurred
at idle and highest levels of total oxides of nitrogen appeared at
full load conditions. Previous survey work had largely been centered
on the use of NDIR instruments for measuring NO only. Nitrogen di-
oxide readings in this program frequently comprised one-fourth to
three-fourths of the total oxides of nitrogen emitted from these
engines at idle. A check of several test power settings using a
NDUV (non-dispersive, ultra-violet) analyzer on an 85 Series engine
at the Bureau of Mines in Bartlesville, Oklahoma, confirmed the
magnitude of N02 readings received on the chemiluminescent analyzer.
The effect of water in the exhaust gas on the reading level of
the chemi+uminescent analyzer was also considered. An ice bath con-
denser was built into the sampling system just before the analyzer
with a by-pass for sample flow either through or around the condenser.
Dry ice was used to assure adequate condenser temperature differen-
tials. Wet and dry NO - NO readings are tabulated below for the
x
GTCP85-l80, SIN P-593 for probe location 3.
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AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
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Emission NO NO
x
Power Setting dry wet dry wet
1 (idle) 21.0 21.0 13.6 13.0
22 (full load) 61.0 57.0 50.0 47.0
span gas 49.5 49.5
For the temperature, humidity, conditions of test, and fuel com-
position used, the calculated wet and dry differences at full load
were comparable to the measured values.
Background or ambient hydrocarbon levels were measured in an
enclosed test cell with engines non-operative and at various load
conditions. Readings of 3.0 to 3.5 ppm were considered as average
for enclosed facilities. Two engines tested in open air facilities
were the GTC85-90B, SIN 24504 and the GTC85-90B, SIN 24376 where the
background level was not noticeable.
A brief discussion of the gas analyzer instrumentation used for
this test program, the supply of various gases necessary to serve as
a standard for the gas analyzer instrument calibration, and gas
analyzer instrument performance during the test will appear in the
following paragraphs. Data on hydrocarbon emissions was collected
using two analyzers, the Beckman models 402 heated analyzer and 108A
cold hydrocarbon analyzer. This report presents data entirely re-
sulting from the heated HC analyzer which is generally accepted as
the preferred method since condensed hydrocarbons in the sampling
lines and equipment is less likely to occur. A flame ionization'
detection method is used in both analyzers. The model 402 analyzer
had built in controls for maintaining a 10 feet long sample line above
300°F.
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AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
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Oxides of nitrogen were measured using a Thermo Electron
Corporation (TECO) instrument model lOA capable of NO and NO + N02
measurements, the latter commonly referred to as NO. A thermal con-
x
verter changes the N02 in the exhaust sample to NO since the analyzer
is capable of measuring only NO.
Carbon monoxide and carbon dioxide were both measured on non-
dispersive infra-red (NDIR) analyzers, Beckman model IR31SL.
Hydrocarbon and chemiluminescent analyzer readings measured
emissions on the basis of total wet exhaust products concentrations.
Carbon monoxide and carbon dioxide measurements were taken after a
desiccant removed water vapor from the sample. The heated 10 feet
long stainless steel sample line was connected to the heated hydro-
carbon analyzer where the sample was then divided into cold lines
about 6 feet long for the chemiluminescent, NDIR, and cold hydro-
carbon analyzers.
Gases are required for each analyzer to provide a method of
instrument calibration. Calibration gases are used to set the zero
and span (upscale) adjustment points of the electronic systems and
recorders. In addition to calibration gases, a fuel and air supply
are needed for the hydrocarbon analyzer burners and oxygen is needed
for the chemiluminescent ozonator. The gases and their concentration
levels used for this test are tabulated below.
Hydrocarbon Analyzers - Beckman Models 402 and 108A
Zero Gas
- Purified Air, Hydrocarbon-free grade less than 0.1 PPM
CH4
Span Gas
- Propane,_4.8 and 48.8 PPM concentrations, Balance - Air,
By Scott Research Laboratories
GT-8747-R
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AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
" DIVISION OF" THE GARRETT CORPORATION
Fuel Gas
- 40 percent H2/60 percent He mixture
Burner Air - Same as zero gas
CO/C02 NDIR Analyzers - Beckman Model IR3l5L
Zero Gas - Nitrogen
Span Gas - CO - 508 PPM
C02 - 2.12 percent
By Scott Research Laboratories
NO-NO Chemiluminescent Analyzer - Thermo Electron Corporation
x
Model lOA
Zero Gas - None, zero by turning sample flow off
Span Gas - NO
- 53.2 PPM
NO
x
- 11.2 and 50 PPM
By Scott Research Laboratories
Ozone Generator - 02' commercial grade
Performance of all analyzers used in this program can be judged
as very good. No attempt was made to correlate the validity of all
instrument readings with other instrumental or chemical means for
determining emission concentrations; however, all instruments were
operated in accordance with manufacturer's recommendations and within
specification temperatures.
GT-8747-R
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rn
AIRESEARCH MANUF'ACTURING COMPANY OF' ARIZONA
A DIVISION Of" THE GARRETT CORPORATION
Analyzers of the NDIR type were trouble-free during the entire
test period. The heated FID analyzer burner ignitor circuit was
troublesome in that a frequent transistor failure in the burner
ignition circuit would render the instrument inoperative. The instru-
ment was otherwise faultless, and reliable operation was possible by
using a butane cigarette lighter to ignite the burner.
The chemiluminescent analyzer performed well except for the
equipment required to maintain a vacuum in the reaction chamber.
Vacuum system leaks caused considerable downtime, although usage of
glyptal (red enamel) on plumbing joints external to the analyzer unit
provided an excellent means of locating and repairing vacuum system
leaks. Vacuum pump pipe threads were sealed with a combination of
teflon tape and glyptal.
During testing, the operator of the chemiluminescent and heated
FID analyzers determined the pace for data accumulation. At any
specific power setting the ability to move from one probe location
to another was paced by the chemiluminescent analyzer, which had to
take two readings, NO and NO. A three-way solenoid on the thermal
x
converter plumbing could have reduced measurement time for the 6000
NO - NO readings taken in this program. During engine power setting
x
changes the pace was set by the restabilization time required for the
heated FID instrument and sample line at the new hydrocarbon emission
level. Samples of transient recording charts are provided in Appen-
dix E for review.
Amplifiers for the analyzers were judged somewhat sensitive to
ambient temperature. During this program Phoenix ambient temperatures
rose from about 70°F to II0oF. Direct sunlight on the chemilumi-
escent amplifier created instabilities during ambient temperatures
of about 95°F (in the shade), and shade provided amplifier stability
to about 100oF. All instruments were kept below these temperatures by
blowing cool air from an evaporative water cooler over them.
GT-8747-R
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
/II. DIVISION OF THE GARRETT CORPORATION
Bottled calibration gases had to be turned off after each engine
test; however, there were instances when their valves were inadvert-
ently left open. Most analyzers had a selector valve in the gas
lines helping to prevent excess loss of gases, by having most gases
turned off during instrument operation. The heated hydrocarbon
analyzer had a solenoid valve which closed off the burner fuel supply
but not the high purity burner air. This design provided no backup
valve to the air bottle and permitted the bottle to drain even when
the instrument was not operating.
The quality of one air bottle appeared questionable in one
operating environment. The purity of the air was specified to be
less than 0.1 ppm hydrocarbons and yet an engine operating at maximum
load measured a negative 0.7 ppm on the heated hydrocarbon analyzer.
Subsequent zero checks on the instrument repeatedly showed good
instrument calibration. Similar power settings on other engines
showed values of about 0.3 ppm hydrocarbon and this engine confirmed
the 0.3 value later in the test. Direct sunlight on the air bottle
on a 110°F ambient day was believed to be responsible for vaporizing
condensed hydrocarbons in the bottle, causing the zero gas to increase
its readout level.
GT-8747-R
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AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A DIVISION OF" THE GARRETT CORPORATION
Gas Turbine Enqine Dutv Cycle Determination
Gas turbine engine duty or service cycles vary from one aircraft
application to another. For example, for auxiliary power unit opera-
tion, some operators start the APU as soon as the aircraft touches
ground while others prefer to use the APU only when the main engines
are inoperative during the "park" mode. The FAA certification cate-
gory imposed on an engine add still other differences to a given
engine duty cycle. For example, auxiliary power units on-board Boeing
747 and McDonnell-Douglas DC-10 aircraft were FAA certified under the
"essentia1 power" category whereby APU operation is permitted for
climb-out, inf1ight and descent modes of aircraft operations.
Testimony to on-board APU engine operation differences or duty
cycle differences between commercial airlines applications are shown
in Tables 9, 10, and 11. Each table represents the response to a
duty cycle questionnaire sent to several major AiResearch APU and
propulsion engine customers. Although Customer C did not report
detailed duty cycle information with respect to the aircraft service
cycle, various APU operational times were reported as follows:
Enqine Model
GTCP85-98
and -98CK GTCP85-115 GTCP660-4
Application Boeing 727, -100 BAC 1-11, 400/500 Boeing 747
APU Hours/Duty 1.4 2.0 2.0
Cycle, Avg
APU Hours/Flight 1.3 Est. 2.1 Est. 1. 0 Est..
Hour, Avg.
APU Hours/Year 347,000 100,800 43,000
GT-8747-R
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"'IODoIDt.iIMaZONA
AIRESEARCH MANUFACTURING COMPANY
A ClIVI.IDN 0" TN. --..TT Ca."D."TlQN
u
Aircraft Service Cycle
Operating
Mode
Description
Descent
Airplane approach
to Airport
Light-off of APU after
termination of main
engine thrust reversal
and taxi to ramp
Taxi
Park
Airplane serviced,
cleaned, refueled, and
passengers boarded
Taxi
Taxi to end of runway
Climb
Climb to cruise
Altitude
Application
APU Time/Duty Cycle, Average
APU HourS/Flight Hour, Average
APU Hours/Year
Number APU'S Installed
Hours/Year per APU, Average
OPERATING LOAD CONDITIONS:
TABLE 9
TYPICAL DUTY CYCLES FOR AUXILIARY POWER UNITS (APU)
ON-BOARD CUSTOMER A COMMERCIAL AIRCRAFT
AiResearch Engine Models
GTCP85-98 GTCP85-98CK GTCP85-129 GTCP660-4
A B C A B C A B C A B C
- --...-- -- '. - -- -- ---- .
Not operated Not operated 50% 7 kw 15 min. Not; operated
in flight in flight 20 amp in flight
50",{, 10 kw 5 min. 50",{, 10 kw 5 min. 50",{, 7 kw 5 min. 50"'{' 32 kw 5 min.
(30 amp) (30 amp) (20 amp) (90 amp)
500°F 18 kw 80 min. 500°F 18 kw 107 min. MAX 22 kw 40 min. 80",{, 54 kw 280 min.
(50 amp) (50 amp) EGT (60 amp) (150 amp)
50% 10 kw 5 min. 50% 10 kw. 5 min. 50% 7kw 5 min. 50% 32 kw 5 min.
(30 amp) (30 amp) (20 amp) (90 amp)
Not Operated in Not Operated in MAX. 7 kw 15 min. Not Operated in
Flight Flight EGT (20 amp) Flight
Boeing 727-100 Boeing 727-100/200 Boeing 737 Boeing 747
90 Minutes 117 Minutes 80 Minutes 290 Minutes
1.0 1.4 1.7 1.0
330,000 91,000 220,000 20,000
150 28 73 9
2,200 3,250 3,300 2,220
A = Bleed-Air extraction load operating point,
percent of bleed airflow or operating EGT, OF
B = Shaft load operating point, SHP or kw
C = Engine run time for aircraft operating mode, min.
'tic;)
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AIRESEARCH MANUFACTURING COMPANY OF" ARIZONA
... DIVISION OF nu: aAARII:TT COIiPORATlON
Aircraft Service Cycle
Operating
Mode
Description
Descent
Airplane approach
airport
to
Taxi
Light-off of APU after
termination of main
engine thrust reversal
and taxi to ramp
Park
Airplane serviced, cleaned,
refueled, and passengers
boarded
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Taxi
Taxi to end of runway
Climb
Climb to cruise altitude
Application
APU Time/Duty Cycle, Average
APU Hours/Flight Hour, Average
APU Hour/Year
OPERATING LOAD CONDITIONS:
TABLE 10
TYPICAL DUTY CYCLES FOR AUXILIARY POWER UNITS (APU)
ON-BOARD CUSTOMER B COMMERCIAL AIRCRAFT
AiResearch Enqine Models
A
GTCP85-98
B
GTCP85-98D/W
GTCP85-98CK
C
A
B
C
A
B
C
Not Operated in
Flight
Not Operated in
Flight
Not Operated in
Flight
o
4 min
o
3 min
o
o
o
o
3 min
80"/0
33 min
50 kw
80",,6
50 kw
34 min
90"/0
40 kw
32 min
o
1 min
o
1 min
o
o
o
1 min
o
Not Operated in Not Operated in Not Operated in
Flight Flight Flight
Boeing 727-100 Boeing 727 DC-9
33 min 34 min 32 min
1.2/1 1.2/1 1. 75/1
105,080 99,216 66,680
A = Bleed-air extraction load operating point,
percent of bleed airflow or operating EGT, OF
B = Shaft load operating point, "SHP or kw
C = Engine run time for aircraft operating mode, min
A
GTCP660-4"
B
C
Not Operated in
Flight
o
o
6 min
80"/0
135 kw
135 min
o
o
2 min
Not Operated in
Flight
Boeing 747
143 min
0.8/1
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EB
AI RESEARCH MANUF'ACTURING CCMPANY CF' ARIZCNA
... DIVISION 0" THE GARRETT CORPORATION
TABLE 11
TYPICAL DUTY CYCLES FOR TURBOPROP TPE331 AIRCRAFT PROPULSION
ENGINES AS SUBMITTED BY LIGHI' TWIN ENGINE AIRPLANE CUSTOMERS D AND E
't:IG)
1111-:3
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION Of" THE GARRETT CORPORATION
Because of the limited response to the duty cycle questionnaire,
assistance from the AiResearch Flight Operations Department together
with the information received on revised duty cycle for APU.s and
propulsion engines were determined. Tables 11 and 12 reflect this
representative average or "weighted" duty cycle thought best repre-
senting the majority of engine customers. Subsequent emissions per-
formance relating to engine duty cycles are based on these data. It
is realized that total emissions generated by any product line is
based on an estimated number of the duty cycles performed by the
number of delivered engines at a given time. Tables 3 and 13 summa-
rize these data.
In order to calculate the exhaust emissions formation rate for
each APU "weighted" or estimated duty cycle two simplifying assump-
tions must be made: (1) As observed in the emissions performance
plots in Appendix C, the resultant emissions are relatively insen-
sitive or do not vary greatly with changes in combined bleed/shaft:
load ratio while operating at maxi~um rated exhaust gas temperature.
Therefore, power setting 15, as described in Table 6, was chosen to
represent a fully loaded APU. This power setting presents a b1eed/
shaft load ratio very nearly the same as was reported by customer B
as shown in Table 10 for "park" mode of operation and (2) since air-
craft taxi time represents only a small portion of the overall duty
cycle time, exhaust emissions during the taxi mode will be approxi-
mated by adding the taxi mode time to the park mode time for evaluation
at the park mode emissions levels.
By using the estimated duty cycle times shown in Table 12 and
these simplifying assumptions, the average exhaust emission formation
rates were calculated and are shown in Table 13.
Because emission formation rates are dependent upon fuel flow,
they are a function of engine size or power. Therefore, a statistical
GT-8747-R
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION Of" THE GARRETT CORPDRATION
TABLE 12
SUMMARY OF ESTIMATED APU DUTY CYCLE TIMES
WITH RESPECT TO COMMERCIAL AIRCRAFT SERVICE CYCLE
Aircraft Service Cycle Approximate APU Time in Mode, min
Operating APU Load APU Size
Mode Description Condition Small Medium Large
Descent Airplane approach to airport Not operated -- -- --
in flight
Taxi Light-off of APU after ter- Max rated 5 5 5
mination of main engine bleed/shaft
thrust reversal and taxi to
ramp
Park Airplane serviced, cleaned, Max rated 30 70 170
refueled, and passengers bleed/ shaft
boarded
Taxi Taxi to end of runway Max rated 5 5 5
bleed/ shaft
Climb Climb to cruise altitude Not operated -- -- --
in flight
(Group I) (Group II) (Group III)
Duty Cycle
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~ AIRESEARCH MANUF''''CTURIND COMPANY 0,. ARIZONA
.. D'"'.''''' D~ YOU a"'..~TT "II."D."~'D"
TABLE 13
SUMMARY OF EXHAUST EMISSIONS FORMATION RATE FOR
AUXILIARY POWER UNITS ON-BOARD COMMERCIAL AIRCRAFT
Formation Duty Formation No. of APUs No. of APUs Operating Time (4) Approximate
GROUP I Sample Rate (1) Cycle Rate Delivered Insta11ed(3) Formation Rate
Size Emission hrs (2) Duty (Approx) (3) hrs/yr/APU by Group,
M!! Application Tested Species Avq, lb/hr Time. lb/ Cvcle (Estimated) Estimated Tons/vr
GTCP30-92 Executive C02 212.0 0.67 142.0 230 160 1,000 17,000
Aircraft CO 0.38 0.25 30
He (hot) 0.007 0.005 1
NOx 0.237 0.159 2
GTCP36-6 Grumman C02 455.0 0.67 305.0 140 95 1,500 32,400
Gulfstrearn II CO 1.39 0.93 99
He (hot) 0.009 0.006 1
NOx 0.72 0.48 51
GROUP II
APU Application
GTCP85-98/CK Boeing 727 9 C02 804.0 1. 33 1,070.0 1,045 2 x 106
GTCP85-98D Douglas DC-9 2 CO 3.04 4.04 790 1,870 2,800 7,958
GTCP85-115 BAC 1-11/400 3 IIC (hot) 0.122 0.162 325 320
GTCP85-129 Boeing 737 1 NOX 1.30 1. 73 335 3400
GTC85-90/90B Ground Cart (5) C02 654.0 0.167 109.0 940 705 1,000 234,000
CO 3.46 0.578 1,237
IIC (hot) 0.018 0.003 6
NOx 0.954 1.59 341
GROUP I II
APU Application
GTCP660-4 Boeing 747 C02 2,867.0 3.0 8,601.0 225 170 2,200
CO 8.82 26.5
HC (hot) 0.394 1.18
NOx 5.42 16.3
TSCP700-4 McDonnell- C02 1,513.0 4,539.0
Douglas DC-IO
CO 0.666 2.00
HC (hot) 0.875 2.62
NOx 4.56 13.35
402,000
1,237
55
760
3.0 (6)
15
1,000
ESTIMATED TOTAL EMISSION
RATE, TONS/YEAR
C02
CO
IIC
1,702
1
7
5
3 x 106
10, 562
383
4,545
NOx
NOTES,
(1)
Formation rates are averaged by groups from emissions performance data reduction printout,
Appendix B, for power setting number 15 (full load) except GTC85-90/90B Ground Cart
operation evaluated at bleed only (power setting number 5).
(2 )
(3)
Duty cycle time from Table 12 and customer survey results.
Approximate number as of end of May, 1971.
delivered APUs.
Installed APUs represent about 75 percent
(4)
(5)
Estimated from Table 9 and Field Service sources.
Used for starting 707, 720, and DC-8 aircraft and emergency starting of other APU on-board
aircraft.
(6)
(7)
Not in service at this time.
Estimates based on same duty cycle as 660-4 APU.
Engines tabulated under each of the above groups do not constitute all engine or aircraft
types in service.
GT-8747-R
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AIRESEARCH MANUF'ACTURING COMPANY OF' ARIZONA
A DIVISIDN Df" THE GARRETT CDRPDRATIDN
evaluation of formation rates based on all the auxiliary power units
sampled, as a single family, is not possible. However, emission
index, Ib pOllutant/lOOO Ib of fuel consumed, is independent of fuel
flow and engine size. Therefore, a statistical evaluation can be
made and is presented as Table 14. As is shown in the table out of
the 26 engine sample size, four engines could not be included in a
single hydrocarbon family and two engines could not be included in
the nitric oxide or total oxides of nitrogen sample family because
the data fell outside of the three sigma deviation from the mean.
GTCP85-98D, SiN P-15541 and GTCP85-98, SiN P-27857 engines did not
conform to the single family statistical test on hydrocarbon emissions.
At an equivalence ratio of about 0.28, signifying maximum load con-
ditions, on page 4, Figure 1 and on page 45 of Appendix C shows these
two units to exhibit obviously higher hydrocarbon emissions than the
remaining lists of 85 Series engines tested. Also note that these
were overhaul engines as shown in Table 4.
Similarly, the two TSCP700-4 engines tested did not conform to
a single family sample test on hydrocarbons, NO, and NOx emissions.
If the auxiliary power units were to be emissions limited based
on the emission index for each then the AiResearch sample family of
APU's, excluding the TSCP700-4, would conform to the following upper
control limits of emission index values:
3.211 for C02
31.48 for CO
0.921 for HC(hot)
4.363 for NO, and
7.708 for NOX as given in Table 14.
In order for emission formation rates to be considered for
statistical comparisons a reduction of data could be made on a brake
GT-8747-R
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AIRESEARCH MANUF'ACTURING COMPANY OF' ARIZONA
A DIVISION 0,. THE GA.RRETT CORPORA.TION
TABLE 14
STATISTICAL EMISSIONS RESULTS FOR AIRESEARCH
GAS TURBINE AUXILIARY POWER UNITS
(AS SINGLE FAMILY OF 26 ENGINES AT FULL-LOAD
EGT AND ENGINE POWER SETTING 15)
Emission
Sample
Size
Conforminq
Basis Two-Sided 95-percent Probability Tables
Sample Mean
Emission Index
LB/IOOO LB Fuel*
Sample
Standard
Deviation
Tolerance Interval to
Contain at Least 99-
Percent of the Population
Lower Limit Upper Limit
Confidence Interval to
Contain the
Population Mean
26 3.148 LB 0.0176 3.084 to 3.211 3.141 to 3.155
C02 LB Fuel
CO 26 11.740 5.54 0 to 31.48 9.444 to 14.035
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lQ r HC (HOT) 22 0.223 0.184 0 to 0.921 0.132 to O. 314
CD 00
--.J (AS CH.4)
'-101:>0 NO 24 2 . 65 9 0.471 0.955 to 4.363 2.454 to 2.864
t\) --.J
I
::0 NO 24 4.928 0.769 2 . 147 to 7.708 4.593 to 5.262
(Ag N02)
*Except as noted.
NOTES:
1.
Engine Power setting reference number 15 represents a combination load comprised of shaft
load and approximately 50 percent maximum bleed air extraction load to the maximum rated
exhaust gas temperature, EGT.
2.
Sample size conforming to statistical test is based on a 3-sigma sample standard
deviation from the sample mean.
3.
Four engines did not conform to HC sample family: GTCP85-98D (SIN P-27857),
GTCP85-98 (S/~ P-15541), and each of the 2 TSCP700-4 tested.
4.
Both TSCP700-4 engines did not conform to the NO and NO sample family.
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AIRESEARCH MANUF'ACTURING COMPANY OF' ARIZONA
A DIVISION OF THE GARRETT CORPORATION
specific emission formation rate basis, defined as lb/Bhp hr, to
determine if the principles of statistics can be applied to the data.
As for the average emission formation rate calculations for pro-
pulsion engines, special significance lies in the fact that they can
be compared to piston-engine light aircraft emissions results as shown
in Reference 1 or be used as an approximation of the absolute value of
emissions generated by turboprop aircraft in the vicinity of airports.
The list of references are included at the end of this section. Con-
sideration has been given to two aircraft service cycles: (I) takeoff-
cruise-landing and (2) landing-takeoff evaluated under 3000 feet as
suggested by the Air Pollution Control Office in Reference 2.
Table 15 shows the average emission formation rates for a com-
parable range of power settings for the test load conditions and duty
cycle load conditions for a four turboprop engine sample. Table 16
shows the estimated duty cycle times in each moqe, the correspond-
ing generated emission weight for time in mode together with emis-
sions in pounds generated for each aircraft service cyc'le, and the
total emission formation rate per year for 80 percent of all turboprop
engines delivered to customers estimating each customer operates his
respective aircraft 750 cycles per year.
Table 17 presents a statistical analysis based on emission index
or mole percent for C02 for a four turboprop engine sample. It serves
only to show that for a 95 percent probability that 99 percent of the
total population existing can be represented by this sample then the
upper control limit for the emission index for C02 must be 3.270
rather than 3.155, CO must be 6.679 instead of 1.489, HcH must be
6.169 rather than 0.845, and NO must be 28.31 rather than 9.930.
x
The high upper limit is a result of 8.3 standard deviations being
required for an engine sample size of four which illustrates the need
for a larger sample size if a high assurance of conforming to a sample
family is desired.
GT-8747-R
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AIRESEARCH MANUF'ACTURING COMPANY OF' ARIZONA
A. DIVISION Of'" THE GARRETT CORPORATION
TABLE 15
AVERAGE EMISSIONS FORMATION RATES
FOR FOUR TURBOPROP (TPE331/T76) .
PROPULSION ENGINES
I At Test Load Conditions I
Test Percent
Power Power, Avg.
Setting
1 0.4
gnd. idle
2 6.0
fIt. idle
I
6 30.0
11 53.2
16 74.4
20 91.5
Avg. Emission Formation Rate,
1b/hr
C02
CO
HC (hot) NO
(as methane) x
(as N02)
3.28 0.237
0.858 1.12
0.331 1. 67
0.088 2.30
0.047 3.00
0.031 3.60
241. 0 3.55
489.0 3.70
653.0 2.96
833.0 2.15
997.0 1.12
1149.0 0.552
I At Duty Cycle Load Conditions I
Avg. Emission Formation Rate, 1b/hr
Operating Percent C02 CO HC (hot) NO
Mode Power, Avg. (as methane) x
(as N02)
idle-taxi 15 550.0 3.42 0.66 1. 33
descent/ 30 653.0 2.96 0.331 1. 67
approach
run-up/hold 50 809.0 2.26 0.120 2.24
cruise 90 1136.0 0.60 0.032 3.55
take-off/ 100 1225.0 0.269 0.023 3.90
climb
GT-8747-R
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[ffi
AIRESEARCH MANUFACTURING CDMPANY DF ARIZDNA
A DIVISION 0" nu: OAAAI:TT CORPORATIDN
TABLE 16
AVERAGE WEIGHT OF EMISSIONS GENERATED DURING EACH
OPERATING MODE OF AIRESEARCH TURBOPROP (TPE33l/T76) POWERED AIRCRAFT
Emission Weiqht for Time in Mode, lb
Aircraft Percent Approximate He (hot) NOX
Operating Max Rated Time in Mode
Mode Description Power (minutes) C02 CO As CH4 As N02
Ground idle Engine startup and taxi 15 5 45.8 0.285 0.055 0.111
to end of runway
Run-up Check out at end of 50 2 26.9 0.075 0.004 0.074
runway
Initial climb Take-off and climb to 100 3 61.2 0.013 0.001 0.195
3000 fee.t
Final climb Climb to cruise 100 7 142.9 0.031 0.003 0.455
altitude (over 3000
feet)
Cruise (Not pertinent to pol- 90 30 568.0 0.300 0.016 1.775
lution near airport)
Inital descent Descend to landing 30 10 108.9 0.493 0.055 0.278
pattern altitude of
'tic;) 3000 feet
J;1
rooo Cruise pattern Hold in landing pattern 50 2 26.9 0.075 0.004 0.074
-oJ
-oJ*" at 3000 feet
lI1-oJ
J
::0 Final approach Descend from 3000 feet 30 2 21.8 0.100 0.011 0.056
and land
Ground idle Taxi back to hanger 15 ...1. 18.3 QdM 0.022 0.044
Takeoff-Cruise-Landing Cycle, TCL TOTAL 63 1,021.0 1.486 0.171 2.362
Landing Takeoff Cycle, LTC TOTAL 16 201. 0 0.662 0.097 0.554
TOTAL EMISSIONS FORMATION RATE, TONS/YR
TCL Cycle 462,000 673 77
1070
LTC Cycle
91,000
300
44
250
NOTES:
1.
Emissions weight data based on emissions formation rates shown on Table
for 4 engines tested.
Emissions data in tons/yr based on information provided by AiResearch Flight
Operations Department and customer surveys. An estimated 80 percent of 467
engines. sold through May 1971 are in active service and reflect an estimated
750 duty cycles per year (about 2 per day) per engine.
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AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A DIVISION Of'" THE GARRETT CORPORATIDN
TABLE 17
STATISTICAL EMISSIONS RESULTS FOR FOUR AIRESEARCH
TURBOPROP PROPULSION ENGINES
UNDER MAXIMUM SHAFT LOAD
Emission
Sample
Size
Sample Mean
Emission Index
LB/1000 LB Fuel*
Basis Two-Sided 95%
Tolerance Interval To
Contain at Least 9~~
of the Population
Sample
Standard
Deviation
Probability Tables
Confidence Interval To
Contain the
Population Mean
C02 4 3.155 LB/LB 0.013 3.045 to 3.270 3.136 to 3.179
Fuel
CO 4 1.489 0.604 0 to 6.679 0.494 to 2.483
HC (HOT) 4 0.845 0.620 0 to 6.169 0 to 1.865
(as CH4)
NOx 4 9.930 2 .140 0 to 2 8 . 31 6.400 to 13.45
(as N02
*Except as noted
NOTES:
1. Sample size conforming to statistical test is based on a 3-sigrna sample standard
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."RESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVI!UCN 0" THE GARRETT CORPORATION
The statistical information generated from both APU and
propulsion engine data leads to one observation. That is, a statist-
ical definition of upper emissions levels that would include a high
proportion of an existing gas turbine population is not considered
practical. This is because emissions levels of identically designed
production gas turbines vary by such large amounts that a statistical
upper control limit to include a high percentage of an existing popula-
tion becomes unreasonably high.
GT-8747-R
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AIRESEARCH MANUF"ACTURING CCMPANY CF" ARIZCNA
A DIVISION Of' THE GARRETT CDRPORATION
REFERENCES
1.
"A Study of Exhaust Emissions From Reciprocating Aircraft Power
Plants." Scott Research Laboratories, Inc., APCO Contract CPA
22-69-129, December, 1970.
2.
"Role of NAPCA in Controlling Aircraft Pollutant Emissions."
paper 710338 by Kittredge G.D. and McNutt B.D., National Air
Polution Control Administration.
SAE
3.
"Measuring Gaseous Emissions From an AirCraft Turbine Engine."
SAE paper 700249 by Chase J.O. and Hurn R.W., u.s. Bureau of
Mines, April, 1970.
4.
"The Current and Future Basis for Aircraft Air Pollution Control."
SAE paper 710339 by William T. Westfield, FAA.
5.
"Procedure for the Continuous Sampling and Measurement of Gaseous
Emissions from Aircraft Turbine Engines." SAE E-3l Committee
Final Draft, May 25, 1971, R.W. Hurn, Chairman, u.S. Bureau of
Mines, Bartlesville, Oklahoma.
6.
"CRC Evaluation of Aviation Emission-Measurement Techniques."
SAE paper 700338 by T.O. Wagner, American Oil Company, April, 1970.
7.
"Fundamental Processes Controlling the Air Pollution Emissions
from Turbojet Engines." AIAA paper 69-1040 by R.F. Sawyer,
University of California, October, 1969.
8.
Clean Air Ammendments of 1970, Congressional Record-House,
December 17, 1970.
GT-8747-R
-------
6.
CONCLUSIONS
-------
ffi]
6.0
6.1
AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISIDN DF" THE GARRETT CORPDRATIDN
CONCLUSIONS AND RECOMMENDATIONS
Conclusions
Baseline exhaust emissions levels have been successfully deter-
mined as requested under Contract 68-04-0022 with the Environmental
Protection Agency, Office of Air Programs for the specified AiRe-
search commercial auxiliary power and propulsion gas turbine engines
used in aircraft-related applications. Two notable conclusions de-
rived from this test program are as follows:
(b)
(a)
A large variation in exhaust emissions test results was ob-
served for several engines tested, particularly emissions
sampled on the 85 Series engines. As Figures 1 through 4
in the Summary, Section 2.0 illustrates; a wide band of
emissions levels over the equivalence ratio or engine load
range exists and covers two orders of magnitude on the
emission index. This characteristic may be attributed
primarily to the combustor related-components of 85
Series engines.
The differences in emissions measurements that resulted
from the various probe measuring techniques used in this
test program suggests the need for additional comparison
studies on a larger number and variety of gas turbine
engines. Since the l2-point fixed (averaging) probe and
movable sampling probe was used to obtain emissions data
for only one engine test, a preference for either prob~
technique is not justified. However, the error expected
from using the l2-point averaging probe was considerably
less than the variation in emissions levels observed for
two engine models having identically designed hardware.
GT-8747-R
-------
EE
AIRESEARCH MANUF'ACTURING COMPANY OF' ARIZONA
A DIVISIDN DF' THE GARRETT CDRPDRATIDN
6.2
Recommendations
Since emissions test results varied significantly in tests con-
ducted on engines that contain identically designed hardware, several
recommendations are in order.
For any given engine model, such as the GTCP85-98, a stu~y should
be conducted to determine why sizeable emissions differences exist
from one set of hardware to another.
Test and study efforts should be conducted to determine the
effects of combustor related parameters such as fuel pressure, fuel
droplet size, spray angle, mixing effects, and combustor installation
orientation on emissions levels. This effort would also have to be
related to the formation chemistry processes.
A study of the kinetics of the formation chemistry processes of
hydrocarbons, carbon monoxide, and oxides of nitrogen, and the relation-
ship of these processes to existing combustion systems tested under
this contract is recommended.
A larger quantity of engines should be sampled in the 30, 36,
660, 700, 731, and 231 Series. One and two engine sample sizes are
not sufficient to establish representative emissions data. A minimum
of a 3 to 4 engine sample size is recommended although 8 to 10 is
preferred.
A comparison of emissions index in 1b/1000 lb fuel consumed
does not give a fair evaluation of engines with different thermal
efficiencies since two engines with the same emissions index could
develop different horsepowers. Therefore, a brake specific emissions
index in lb/Bhp x 1000 lb fuel consumed and a brake specific formation
rate in lb/Bhp hr is a more reasonable comparison for engines wi~h
GT-8747-R
-------
~
AIRESEARCH MANUF'ACTURING COMPANY OF' ARIZONA
A. DIVISIDN OF' THE GARRETT CORPORATION
different thermal efficiencies or different duty cycles. For bleed
engine evaluation, the pressure-volume (pv) work delivered to the
aircraft bleed system should be evaluated as available power for the
brake specific calculations.
The evaluation of emissions on a brake specific basis would give
renewed support the possibility of statistical study of various
engine sizes in a single family comparison.
GT-8747-R
-------
-------
~
AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A DIVISION DF' THE GARRETT CORPORATION
A.
ANALYZER INSTRUMENTATION
This section reviews the gas analyzers and their principles of
operation as used to conduct emissions measurements at AiResearch
facilities.
A.1
Heated Hydrocarbon Analyzer (Beckman Model 402)
The hydrocarbon analyzer, Figure A-1, is designed to measure the
total hydrocarbon contents of exhaust emissions from gasoline, diesel,
gas turbine, and jet engines. The analysis is based on flame ioniza-
tion, a highly sensitive detection method.
The instrument consists of:
( 1)
Heated, temperature-controlled sample line.
(2)
Analyzer unit, incorporating a flame-ionization detector and
associated sample-handling system, with critical sample-
handling components contained within a temperature-
controlled oven.
( 3)
Electronics unit, containing an electrometer amplifier and
associated circuitry, readout meter, and recorder output
provisions. The electronics unit is attached directly to
the analyzer unit as shown in Figure A-1.
Sample from the source is drawn into the analyzer through the
sample line. To prevent the loss of higher-molecu1ar-weight hydro-
carbons, the sample is maintained at an elevated temperature during
its passage through the sample line and the interior of the analyzer.
Temperature setpoint for both the sample line and the analyzer oven
was 310°F for the tests carried out in this report.
GT-8747-R
Appendix A
-------
J
E-;:?
AIRESEAR,CH MANUF"ACTURING COMPANY OF" ARIZONA
A DIVISION OF" THE GARRETT CORPORATION
~
"
o
Access Door for Burner,
Sample Pump, and Gas
Selector Valve
o
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~ i ! OVEN
W E
- .
o >-
] ~ SAMPLE
,n LIINE
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ANALYZER
UNIT
* NOTE: Electronics Unit may be detached from Anal~zer
Unit, for remote mounting ot maximum distance of
75 feet.
ELECTRONICS UNIT *
01
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A, ANALYZER UNIT
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14, SAMPLE/CALI BRA TE
Gas Selector Volve
13. Sample Bypass V;, 15. Oven T "mperoture Meter
Flowmeter ~-",",-...", ~
12. SP AN Gas ~
Flow Control Valve " -
a.-
E e
16. TEMP. ADJUST " -
>- c
11. ZERO Gas Control 0
Flow Control V olve ~u
-
~ 17. HEATER 0
10. SAMPLE Gas
a Pressure Gauge Indicator Lamp
U
- 9. SAMPLE Gas
0 Pressure Regulator
"
8. FUEL Gas I 1. POWER Sw;tch
Pressure Gauge -
7, FUEL Gos ,,1 2. FLAME OUT 1
Pressure Regulotor Indicator Lamp 0
U
6. AI R Pressure 3. FUEL SHL! Y.OFF a
o
Gouge Override Switch ~
5. AI R Pressure 4. IGNITE Sw;tch u:;
Regulator
o
- I
01
~
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HYDROCARBON ANALYZER (BECKMAN MODEL 402)
(COURTESY BECKMAN INSTRUMENTS, INC.)'
FIGURE A-I
o
MP-30224
GT-8747-R
Appendix A
Page 2
-------
~
AIRESEARCH MANUF'ACTURING COMPANY OF' ARIZONA
A DIVISION 0" THE GARRETT CORPORATION
The hydrocarbon sensor is in a burner where a regulated flow of
sample gas passes through a flame sustained by regulated flows of a
fuel gas and air. The flame formed when fuel gas (hydrogen diluted
with an inert gas) burns in air contains an almost negligible number
of ions. Introduction of traces of hydrocarbons into such a flame,
however, produces a large amount of ionization. Within the flame,
the hydrocarbon components of the sample stream undergo ionization,
producing electrons and positive ions. Polarized electrodes collect
. \
these ions, causing current to flow through measuring circuitry
located in the electronics unit. The ionization current is propor-
tional to the rate at which carbon atoms enter the burner and is
therefore a measure of the concentration of hydrocarbons in the
original gas sample.
The flow diagrams for the analyzer and burner are shown in
Figure A-2. A stainless-steel bellows-type positive displacement pump
of four cu ftjmin capacity draws the sample into the analyzer and
through a glass fiber filter that removes particulate matter. The
sample is then supplied to the burner under positive pressure. An
internal sample-bypass arrangement provides high-velocity sample flow
through the analyzer, thus minimizing system response time. A front~'
panel flowmeter indicates bypass flow. Since the ionization level is
related to the floW rate of sample through the flame, the flowmeter
must be set to read a sample flow identical to the calibration gas
flow. The analyzer has rear-panel inlet ports for connection of
suitably pressurized zero and span standard gases. Flow of each
standard gas is controlled by a corresponding front-panel needle
valve. A front-panel three-way valve permits selection of either the
actual sample or the desired standard gas (i.e., "zero gas" or "span
gas" referenced in Figure A-2) used in calibrating the instrument.
The oven, which uses
selected temperature by a
ing a thermistor sensor.
air-bath heating, is maintained at the
solid-state temperature controller utiliz-
A vertical partition divides the oven into
GT-8747-R
Appendix A
-------
Ea
AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A DIVISION Of' THE GARRETT CORPORATION
AIR
INLET
flL TER
D
FUEL
GAS
INLET
. TEMPERATURE-CONTROLLEOI
SAMPLE LINE
ZERO
GAS
INLET
SPAN
GAS
INLET
VALVE
AIR
REGULATOR
RESTRICTOR
GAUGE
~
r---"'--,I
I I
I BURNER I
I J... I
I V I
I I
I I
I
I
I
I
SAMPL E
CAPILLARY
I
I
I
SAMPLE I
BYPASS
'::"
SAMPLE
-=
TEMPERATURE-
CONTROLLED OVEN
------
CHIMNEY
IGNITOR DISCHARGE PDINTS
THERMISTOR SENSOR FOR
BURNE.FLAMEOUT/FUEG
SHUTOFF CONTROL CIRCUIT
SHIELD ASSEMBLY
ANODE TERMINAL
COLLECTOR ASSEMBLY
ELECTRODES
HOUSING
JET
AIR INLET
BASE
'::" BYPASS
-::-
-::-
=-
::-
~ ~:1
I
I
------...1
FIL TER
REGULATOR FLOWMEiER
FLOW DIAGRAM
SPECIFICATIONS'
. Analysis Temperature. . . . Adjustable Irom 200 0 F to 400 0 F
Line Voltage............. 107-127 VAC. 50/60 Hz,
1000 watts max. .
Ambient Operational
Temperature.......... 32 0 F to 110 0 F
Ambient Operational
Humidity. . . . . . . . . . . . . 95% R.H.
Potentiometric Output. . . . 10 mV, 100 mV, 1V
Sensitivity. . . . . . . . . . . . . . 5 ppm to 10% lull scale as CH.
with H,/N, or H,/He Fuel
Ranges .................X1, X5, X10, X50, X100. X500,
X1000, X5000 with continuous
electronic span adjustment
Response. . . . . . . . . . . . . . . less than 1 second for 90~o of
linal reading (with CH. Irom ana-
lyzer input without sample probe)
Electronic Stability. . . , . . . :!: 1 % lull scale /24 hrs. with less
than 10. ambient temperature
change.
Repeatability............ :!:1% lull scale lor successive
samples
Temperature Controlled
Pr.obe ................10 It. length, tellon surface in con-
tact with sample (proportional
temperature controlled and ad-
justable from 200 0 ~ to 400 < F)
BURNER DIAGRAM
HEATED HYDROCARBON ANALYZER SPECIFICATIONS AND DIAGRAMS
- .
(FIGURES COURTESY OF BECKMAN INSTRUMENTS, INC.)
FIGURE A-2
GT-8747-R
Appendix A
Page 4
-------
~
AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION OF' THE GARRETT CORPORATION
two compartments with separate doors. The left-hand compartment con-
tains the burner, the sample pump, and the three-way gas-selector
valve. The right-hand compartment contains only the sample filter and
permits access to the filter without disturbing temperature equilib-
rium of the other elements.
Within the analyzer, the fuel gas is routed to the burner through
a solenoid valve controlled by the burner-flameout/fuel-shutoff cir-
cuitry. A thermistor sensor continuously monitors the status of the
burner flame. In event of flameout, the valve closes to stop the flow
of fuel gas; simultaneously, a front-panel indicator illuminates to
alert the operator.
The electronics unit has front-panel controls for range selec-
tion and adjustment of zero and span. Readout is on a front-panel
meter calibrated linearly from 0 to 100. In addition, a selectable
output of 10 mv, 100 mv, or 1 volt is available to drive a voltage-
type recorder.
A.2
Cold Hydrocarbon Analyzer (Beckman Model 108A)
The cold hydrocarbon analyzer (Figure A-3) continuously monitors
the hydrocarbon content of a cold sample gas stream. This instrument
also uses the flame ionization method of detection (FID) by measuring
the concentration of carbon ions released by a sample gas passing
through a burner.
This analyzer differs from the heated hydrocarbon analyzer in
that it contains no built-in sample pump, heated sample line controls,
oven, or fuel shutoff safety devices. Although the burner configura-
tion (Figure A-3) is geometrically different than the heated analyzer,
any differences in readings between the two analyzers have been
GT-8747-R
Appendix A
Page 5
-------
~_.
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... CIVI81CN CI" THE OAFUIETT COillPOill"TJON
Meter
LJ
Attenuatar Switch
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Inner Door l.tch
Outer Door
Power Switch
Zero Adjust
FRONT VIEW WITH OUTER DOOR OPEN
o
MODEL IOBA PANEL.MOUNTED HYDROCARBON ANALYZER
la:nJlorCor.tacts
I
I
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~
01
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Burner ChImney Assembly
lanltor(Rhodlum)
Collector (Stainless Steel)
o
~
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Combustion Chamber
o
Burner Jet Contact
o
J
J
Sample Gas In
o
BURNER ASSEMBLY (WITH CAPILLARIES ATTACHEDI
COLD HYDROCARBON ANALYZER AND BURNER ASSEMBLY
ICOURTESY BECKMAN INSTRUMENTS, INC.]
Q
FIGURE A-3
o
GT-8747-R
Appendix A
Page' 6
-------
~
AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
"DIVISION OF THE GA.RRETT CORPORATION
attributed to condensation of the higher molecular weight hydrocarbons
in the sample and analyzer lines, resulting in lower readings for the
cold FID instrument.
For this test program, the cold FID analyzer was used in addition
to the heated FID analyzer for sampling the first engines. Sample was
brought through ten feet of heated sample line to the hot FID analyzer
and then divided with an additional six feet of the line to the cold
FID analyzer. Both instruments were calibrated on the same zero and
span gases such that instrument readout differences are attributable
primarily to the cold sample line.
A flow diagram of the cold FID system is shown in Figure A-4.
A.3
ChemiluminescentjNO - NO Analyzer
x
The chemiluminescent analyzer is packaged as four separate units:
(1) control unit, (2) an analyzer unit, (3) a reaction chamber mechan-
ical vacuum pump, and (4) a converter for the thermal conversion of
N02 to NO. For these tests, a Thermo Electron Corporation analyzer
model lOA was used, which was operated in the NO and NO modes.
x
A typical arrangement of the Model lOA chemiluminescent analyzer
is shown in Figure A-5. Other equipment needed for use with the ana-
lyzer are the NO and N02 standard gases, an oxygen source for the
ozone generator, and an accumulator and suitable sample bypass pump to
provide two to two and one-half cu ft/hr sample flow.
The control unit contains the switch for selection of sensitivity
from seven available full-scale ranges (10, 25, 100, 250, 1000, 2500,
and 10,000 ppm) and potentiometers which provide for instrument
calibration.
GT-8747-R
Appendix A
-------
'1j:J>lG1
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AIR£S£ARCH MANUFACTURING COMPANY OF ARIZONA
A OlVISION 0,. THI[ aA'UU:TT CDRPORAT10N
Edemat Air Pressure
Regulator and Gauge
r----------------------------~
I
Filter
Air
Pressure at Inlets
30.150 psig
Internal
Air Pressure
fi.ea:ul,tor
External Fuel Pressure
Regulator and Gauge
Each Regulator Adjusted 50 Corresponding
Gauge Shows 25 p$li
Internal
Fuel Pressure Regulator
Internal
Fuel Pressure Gauge
Filter
Fuel Flow Rate 75' cc/min.
Air Flow RlIte
325 -385 cc/mln.
Fuel (40% HI;
60% Hz)
~ Pressureatlnlel Spslg
Flow of SamDle in Standard Model l08A - - - - - - - - - - - - - - - - - - - - - - - - - -
(not equipped with pump accessory) --- - - - --- - - -- - - - - - - - - - -~,
I Ii
II
I
I II
II
I Pump I
O II
Sample Flow I
Flow of Sample in Model tOgA (or model - =-=..,- - - - - - - - - - - - - - - - - J,
l08A equipped with pump accessory) -- - - _1-- - - ~- - - - - - - - --
Rate 1- 5 lIter/Mln
NOTE:
STANDARD FLOW CONFIGURATION, SUITABLE fOR MEASURING
HYDROCARBON CONTENT OF ALMOST ANY GAS OR MIXTURE OF GASES
HYDROCARBON A"ALYZEI
-----------
Exhaust Gas Out
Burner
Sample Bypass
Out
Sample Pressure Regulator,
I
I
I
I
-------~
-----------
*This regulator must be set at least 5 psi above pressure of
internal reeulator. Minimum permissible prenure mus.t be
determined experimentally.
COLD HYDROCARBON ANALYZER FLOW DIAGRAM
----- ---.--
ICOURTESY OF BECKMAN INSTRUMENTS, INC.I
-------
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A OIVIBICN OF' THE GA.RRETT CORPORATION
oIii
iii
PM
-------
~
AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION or THE GARRETT CORPORATION
The analyzer unit contains the reaction chamber, the photo-
multiplier tube, the ozonator, the ozonator power supply, the oxygen
and gas sample lines, capillaries, and pressure regulators.
Figure A-6 presents a schematic drawing of the entire chemilumi-
nescent instrument with the portion inside the dashed rectangle repre-
senting the analyzer unit. The heart of the analyzer is the cylin-
drical reaction chamber where sample gas containing NO molecules mixes
with 03 molecules from the ozonator. Electronically excited N02 mole-
cules are created that emit light (chemiluminescence) as the orbital
electrons decay to their ground states.
The chemiluminescence is monitored through an optional filter by
a high sensitivity photomiltiplier positioned at one end of the
reactor. The filter-photomultiplier combination responds to light in
a narrow wavelength band unique to the desired electron decay. Sample
flow is controlled so that the output from the photomultiplier is
linearly proportional to the NO concentration.
Oxygen, 02' enters the analyzer unit, passing through a pressure
regulator that is used to regulate the flow rate, and enters the
ozonator. A fraction of the 02 is converted to 03' and the mixture
passes through an orificing glass capillary to the reaction chamber.
Sample gas enters the instrument, passing through another glass
capillary, and is bled off to the reaction chamber. That portion of
the entering sample not diverted to the reaction chamber passes
through a front panel flowmeter adjusted to two standard cubic feet
per hour and a regulator to the instrument exhaust system. A bypass
pump is used to pull the sample through the instrument. That portion
of the entering gas sample diverted toward the reaction chamber is
directed to the rear of the analyzer unit, where the sample gas will
GT-8747-R
Appendix A
-------
'tI>c;)
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AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A DIVISION 0" THE: GARRETT CORPORATION
VACUUM PUMP
LEGEND
------- ELECTRICAL CONNECTION
GAS CONNECTION
fr":.::.--------":::. ~~
.-----------------------,:------ -----------------------------------,
I m:-l ~ REFERENCE , I
I ~ ~ REACTION +- I
I II CAP I LLARY CHAMBER I
I "0.008 X 11/2 IN. ' SAMPLE I
I OZONE ---- SAMPLE GAUGE I
I GENERATOR ~ -+ -+ +- REGULATOR I
I OXYGEN SAMPLE I .
I OXYGEN t VALVE VALVE -+ I .
I GAUGE I
I PHOTOMULTIPLIER OPTICAL I
I FILTER FLOW I .
I METER I
I II Ii t CAPILLARY ~ CAPIkLARY I
OXYGEN :1 :1 0,005 X 0 020 X I
I REGULATOR :! :i 1 1/8 IN. ] [-- '.' I
I II " ~ 1 1/2 I I
I t :: :1 , t ... I
II :1 I
I NO. ANALYZER UNIT :I:i . I
L____- ----------------------1:---::----------- ---- ------- -- _..J
" I,
,I "
:: II SAMPLE BYPASS AI R
,I " IN
,I ,I
!! 'I
OXYGEN
N02 ~ NO
CONVERTER
AMPLIFIERI
CHEMILUMINESCENT ANAL YlER
-------
~
AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION OF" THE GARRETT CORPORATION
enter the
( i . e ., NO
converter if the instrument is operating in the NO mode
x
- N02 mixture mode). As explained below, use of the con-
unnecessary if the instrument is operating in the NO mode.
verter is
The basic chemiluminescent analyzer is only sensitive to NO mole-
cules, as opposed to N02 molecules, since 03 does not react with N02
to create chemiluminescence. Therefore, to measure NOx (N02 + NO) ,
the N02 must first be converted to NO. The conversion is accomplished
by passing the sample gas through the converter, a thermally-insulated
resistance-heated stainless steel coil at 1292°F. With the applica-
tion of heat, N02 molecules in the sample gas are reduced to NO mole-
cules. Two three-way valves located on the front of the converter
direct the sample gas either through the converter to measure NO or
x
past the converter to measure NO.
A precision Scientific company mechanical vacuum pump, Model
S-35, is supplied to evacuate the analyzer reaction chamber to pres-
sures in the 5-12 torr range. A photograph of this vacuum pump
appears in Figure A-7. A metal bellows hose connects to a molecular
sieve installed above the mechanical pump. The purpose of this sieve
is to absorb 03 in order to prevent breakdown of the pump oil.
The gas sample is pulled through the instrument by a small dyna-
pump shown together with its specification in Figure A-7, after which
it is exhausted to ambient. This pump improves the overall system
response by moving the flow in the main sample line by about 20 liters
per minute, while each instrument in the analyzer group removes flow
from the main sample line at a much lower rate.
GT-8747-R
Appendix A
-------
"0
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AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
PERFORMANCE SPECIFICATIONS FOR
THE DYNA.PUMP ARE AS FOLLOWS:
Capacity, cu. in.
430
14
Maximum Pressure, psi
Maximum Vacuum, Inches Hg..
14
Strokes per Minute
3000
Motor, H.P.
1/50
5-1/2
Weight, 1bs
OPTIONAL DYNA.PUMP
(i. e., SAMPLE BYPASS PUMP)
., "\
I,f
MECHANICAL REACTION CHAMBER VACUUM PUMP
(PRECISION SCIENTIFIC CO. MODEL 5-35)
VACUUM PUMPS FOR CHEMILUMINESCENT ANALYZER
FIGURE A-7
GT-8747-R
Appendix A
-------
~
AIRESEARCH MANUFACTURING COMPANY OFARIZONA
It.. OIVISION Of' THE GARRETT CORPORATIDN
A.4
Non-Dispersive Infrared {NDIR} Analyzers for CO - C02
To measure the differential absorption of infrared energy, this
instrument employs a double-beam optical system contained in the
analyzer section. A simplified functional diagram and instrument
specifications are shown in Figure A-B.
Two infrared sources are used, one for the sample energy-beam,
the other for reference energy-beam. The beams are blocked simul-
taneously ten times per second by the chopper, a two-sigmented blade
rotating at five revolutions per second. In the unblocked condition,
A of Figure A-B, each beam passes through the associated cell and into
the detector.
The sample cell is a flow-through tube that receives a continuous
stream of sample. The reference cell is a sealed tube filled with a
reference gas. This gas is selected for negligible absorption of
infrared energy of those wavelengths absorbed by the sample component
of interest.
The detector consists of two sealed compartments separated by a
flexible metal diaphragm. Each compartment has an infrared-
transmitting window, to permit entry of the corresponding energy-beam.
Both chambers are filled, to the same sub-atmospheric pressure, ~ith
the vapor of the component of interest. Therefore, each chamber will
absorb infrared energy from its source and will respond.
The response of the two detector chambers differs, since in
operation the presence of the infrared-absorbing component of interest
in the sample streams leaves less energy available for the correspond-
ing detector chamber. There is, thus, a difference in energy levels
between the sample {containing the component of interest} and the
reference (non-absorbing) sides of the system. This energy difference
results in the following sequence of events.
GT-8747-R
Appendix A
-------
rn
A DIVIBION Of' THE GARRETT CDRPDRATION
AIREBEARCH MANUF"ACTURING COMPANY OF" ARIZONA
SPECIFICA TIONS
MAXIMUM ZERO DRIFT:
:t 1 % of full scale per 8 hours.
MAXIMUM SPAN DRIFT:
:!: 1 % of full scale per 24 hours.
SENSITIVITY:
0.5% of full scale.
ACCURACY:
-==1%.
AMPLIFIER RESPONSE SPEED:
90% response in 0.5 second.
AMBIENT TEMPERATURE RANGE:
IR315. IR315L. -20. to +120.F.
OUTPUT (Options Available) :
Current output-O to 5 ma into 500 ohms maximum.
Voltage output-Adjustable to match any potentiometric
recorder having a span of between 1 and 100 mv.
VOLTAGE AND FREQUENCY
(Options Available) :
115 :t15 volts, 60 :to.5 Hz (cps); or
115 ::: 15 volts, 50 :!: 0.5 Hz (cps).
MAXIMUM POWER CONSUMPTION
IR315, 530 watts; IR315L. 640 watts.
MAXIMUM SEPARATION OF AMPLIFIER
CONTROL SECTION AND
ANALYZER SECTION
500 feet.
SHIPPING WEIGHT:
tR315S, 115 pounds; IR315L, 170 pounds.
NET WEHiHT:
IR315S. 85 pounds: IR315L, 120 pounds.
CATALOG NUMBERS:
95700 Model IR315S Infrared Analyzer (Short Path)
95701 Model IR315C I'Ifr'!r"d Analyzer (Long Path)
----~......,. ---~_.-----..". . _...-
100000 I Non-Absorbing
o 0 0 Molecules
e.e...
. ..
Infrared-Absorbing
Molecules
Chopper Moto~
Reference -tW"'f~" ' rT:ll-rcJl- Sample
Source . Source
Chopper' ,i
;.0°0
!>':.i>
~ rooD
~ ?o 0
g :°0,0
~ ~: (>
1V~ooo
C>: I> 0
..: 0
00°
qo 0
p: 00'
i
. .9 t
00'0"[- Sample In ;
~ . o' i
u o. ~ 1
-K ~.o. /\ ['t- \i\iS Nor [;LCc;,lD RY~
~ 0,0 0 n:OH'CR f'\SS nili','UGH'
en .., Cl',LS f\":DIf\lTUO~fH'rORI
o.~ ~
.0 . ~
o 00.0 :
~ ~ :: - Sample Out I
a:; "'..
o '
A
Reference
Chamber
Stationary
Metal Button
Sample
Chamber
Oscillator
Unit
To Amplifier/Control Section
Chopper_otor
Reference W. , W Sample
Source Source
Chopper
00 0
000
= 000
'" 0 .
u 00
Q.J 0 0 0
goo
'" . 0
~ 0
~ 000
cv 000
C>: 0
00
o
. .
0.0
= :: ::[- Sample In
'" .
u 0.0.
.a. . o. 8 ~1F/\i'-:iS RLOC!...EO
~ 0.°. ::y ~"~t-l~lrl':~.;~ D~'i\:\'1
en . 0°. ,\U I r:f.Ti~C.(OR
0.°0
10.. 0.0.
~ : 0.8- Sample Out
'"
Q)
o
B
Stationary
Metal Button
Reference
Chamber
Sample
Chamber
Oscillator
Unit
I._-__~~~~e~~~~~r~,-=-~ctl~ .-
i
,
i
. .- , !
~ ~- -~ -- .-
NON-DISPERSIVE INFRA-RED
ANALYZER SECTION SPECIFICATIONS
AND FUNCTIONAL DIAGRAM
FIGURE A-8
MP-30Z53
GT-8747-R
Appendix A
-------
~
( 1)
( 2)
(3)
( 4)
(5)
AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION Dr- THE GARRETT CORPDRATION
Radiant energy absorption: In the sample cell through which
the infrared radiation passes on the way to the sample
chamber of the detector, part of the original energy of the
sample infrared beam is absorbed by the component of inter-
est present in the sample. In the reference cell, however,
absorption of infrared energy from the reference beam is
negligible, and the energy of this reference beam is higher.
Temperature effect: Inside the detector, each beam heats
the gas in the corresponding chamber, because of absorption
of infrared energy by the component of interest. The gas in
the reference chamber is heated to a higher temperature,
however, since the energy available from the reference beam
is higher.
Pressure effect: The higher gas
ence chamber raises the pressure
that of the sample chamber.
temperature in the refer-
of this compartment above
Mechanical energy effect: The higher gas pressure in the
reference chamber distends the diaphragm toward the sample
chamber. The energy difference between the two chambers in
thus expended in flexing the diaphragm.
Capacitance effect: The diaphragm and an adjacent station-
ary metal button (see Figure A-8) constitute a two-plate
variable capacitor. Distention of the diaphragm away from
the button decreases the capacitance.
When the chopper blocks the beams, as in B of Figure A-8, pres-
sures in the two chambers equalize, and the diaphragm returns to the
undistended condition. As the chopper alternately blocks and unblocks
the beams, therefore, the diaphragm pulses, thus changing detector
GT-8747-R
Appendix A
-------
~
AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A DIVISION OF' THE GARRETT CORPORATION
capacitance cyclically." The detector signal is passed through the
electronic circuitry, where it is treated and sent to a meter and
recorder.
The meter reading is a function of the concentration of the
component of interest in the sample stream. When the instrument is
put into operation, it is adjusted so that a reading of zero or any
desired arbitrary reading corresponds to a concentration of zero per-
cent of the component of interest, while a fu1lscale reading corre-
sponds to the highest concentration in the operating range covered.
Each instrument is provided with a calibration curve for converting
meter readings to concentrations.
GT-8747-R
Appendix A
-------
APPENDIX B
. I
I
\,
-------
~
AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
/II.. DIVISION ElF" THE GARRETT CORPORATION
APPENDIX B
EMISSIONS PERFORMANCE DATA REDUCTION PRINTOUT
GT-8747-R
-------
rn
AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
A DIVISION C,. THE GARRETT CDRPDRATIDN
GROUP 1
AIRCRAFT PROPULSION ENGINES
-------
- - -
c - .' . . EPA-AIRESEARCH EMISSION PROGRAM TEST SUMM~RY
. --~-~--~~-----------:-----"OtltlOtlOtlOOtlOtltltltltltltllltlItOtlOtlOOOtlOo tltltltlOltllOtl It It If 00
. ENGINE TFE 731-2 SIN 1305-2 DATE OF TEST 6/10/71 TYPE OF FUEL ~V.KEROS.
(:=--FUn.!1/C=I.92~-~STOI~HIOMETP.I~' F~A= .0:843 'RATED THRUST= 2~00.0 RATED E~T=1700.0 'DEG.F R4TED SPEED= 21000.0
DEw PT.= 30.0 REL.HUMIDITY= 10.0 PEqCENT SPECIFIC HUMIDITY= .00359 BAROMETRIC PRESSUQE=28.55 IN HGA
( GND IDLE FLT IDLE
'--Po\iER'SETTING NuMBER - ' ,. 1 2' - - -6 -, - 11 -, 16 20-'
PERCENT MAX. THRUST 6.9 14.5 37.3 58.5 79.4 93.0
( DELTA CORRECTED THRUST.LB. 202.3 425.5. 1095.1 1715.6 2328.6 2730.0
---MEASURED-THRUST, LB. - ,--'---'- 193.0----406.0"'1045.0 1631.0 ". 2222.0 2605.0
EAHAUST GAS TEMP.. DEG.F 854.0 945.0 t17f.0 1329.0 1461.0 1537.0
~ SHAFT SPEED, Nl, RPMS160.0 8470.0 13040.0 15710.0 17650.0 18560.0
-----SH4FT SPEED, N2, RPM --, --1f.t800.0 -21070.0' - 25370.0 27020.027960.0 28430.-0 - --
COMPRESSOR INLET TEMP.,DEG.F 91.0 . 89.0 92.0 92.0 91.0 91.0
( COMP~ESSOR DSCHG. PRES.,PSIA 26.338.8 71.5. 95.5 131.5 148.5
.----- COMPRESSOR MAP FLO\~.LB/SEC .. 4.87' 7.58 . - 14.21 - 19.08 . 23. 79 26.~0
FA RATIO BASED ON MAP FLOW .0109 .0113 .0124 .0135 .0145 .0150
, ( CORRECTED FUEL FLOW, LB/HR 177.0 285.0 587.0 858.0 1150.0 1330.0
- >---dFA RATIO'CALC.FRqM EMISSION' .0102 .0109 .0128' .0140 . '.0144.0149-
EQUrV;'L£NCE RATIO .150 .159 - .187 .205 .210 .217
( tI*ootloo*~~oolt***oo*tI*lt*oooo*o*ootltlo**tltI***otl*tltltI*OSUMMARY OF REDUCED EMISSION OATAIIII*tI*tlotltltltlo***olto*lt*o*ooo***ootlo**tI*tlOtlooo~*oOtlOtl
-, ----CAR90,~'DI0XIDE--'--"'" .-...-... .----- .........u. ...--.-- _......._..n__- "0" - --'- - - -- .-.,...... ,.-
- - -
- .
- -
-~-.- --- ------~ ---
- .- ---
-----
.-.. ------- -- --
- --- ----
.-- - --- -----
- -- - ----- ------
, -
, ( -, PERCE 'IT BY VOLUME
. - --- - - LB. C02 PER lB.' OF FUEL
-' wEIG~T FLOW, LB./HR.-
'~( ~'tI:I"~,l CARBON f.10NOX IDE
~:g 71 -
( (1) (1)-0)' PP~' BY vOLUME
~ 8. ~:. .. LB. PER lOOn LR. OF FUEL
~'''j'!: "'EIGHT FLO'-~, LRo/HR.
: ( tII \
. -~-- UNRUR,~ED HYf)ROCAR80NS AS PP1.' CAPQON
- - -. --
2.03 2.20 2.60 2.86 2.93 3.03
3.05 3.10 3.13 - .. 3.15 - '3.15"- 3.15
539.2 B84-.9 183~.8 2699.6 3622.4 4191.4
-.-~ ..-- --- - ------- ----------
463.4 - 263.6 149.3 '. 65.5 37.7 24.7
--44.212 23.f>89- 11.469 -4.585 ' 2.579 1.630
7. H26- 6.751 6.732 3.934 2.965 2.168
- - .--- --
. -,---_. .-. ---.-
-- - --- - ---q---
- - -- ---
- - ----' - - -
I
I ----
C~~ -':~ PPM BY VOLU'!E 253.8 84.7 28.9 3.Q 1.2 .8
--. -'[8~ PER 1000 LA.'OF'FUEL 13.842 4.351 1.268 - .155 .1)48 .031
WEIGHT FLO,;, LB./HR. 2.450 1.240 . i44 .133 .056 .042
, C. -'--- N ITR I C OXIDE
(_. PPM 8Y VOLUME 6.2 14-.5 34.5 58.0 84.6 110.3
Lri. PER'100n LB.. OF FUEL .630' 1.397 2.840 - 4.~49 6.197 7.813
wEIGHT FLO\~, LB./HR. . 112 .398 1.667 3.731 7.126 100391
( ----- NITROGEN DIOXIDE -.. - 4---- -- -- - ---. - ..
( -.- PP~1 AY VOLUME 7.7 - 6.5 8..0 6.8 5.8 6.2
-LBo' PER 1000'LA. OF FUEL 1.204 .965 1.014 .778 .647 .674
WEIGHT FLOw. LB./HR. .213 .275 .595 .667 .744 .897
! ( ----rOUL' OXIDES -OF NITROGE~j AS N02 (3) B- -- ---------- ... - --_.~ .a..-
r PPH BY VOLUME 13.Q i?1.1 42.6 64.8 90.4 116.5
C.... -, -- LB. PEe 1000 L9. OF FUEL 2.111 3.108 5.368 7.445 10.147 12.653
WEIGHT FLOW, LB./HR. .384 .886 3.151 6.38'1 11.670 16.828
--- . - - -- -
- - --- -
L. -_:_--
(
*OOlltl !\lUTES -tlOOOIl
I.ALL EMISStO~S CQvCENTRATInNS CORRECTEn TO CONCENT~ATIO~ IN WET EXHAuST FqOM COMBUSTION WITH DRY AIR.
2.EquIVALE~CE RAT10 CALCULATED FRO~ C02,CO. AND HC DATA AND FUEL COMPOSITION.
3.TnTAI. NTTROr,F..'1 OXIOF5 CAU-:UL,\TF.rJ IIsnG NOX CONCENTRATION ANI) ~1()LECULI\R wqG!-iT OF N02 ('06.0\1.
-
-------
~
ENGINE
TSE231-1
?301-10
EPA-AJRESEARCH E~ISSIn~ P~OGRAM TEST SU~~ARY
00000000***0000000000*00000000000*00*000000000
DATE Of TEST b/18/?1 TYPE OF ~UEL JP5
FUEL H/C=1.877 STOIC~IO~ETRIC F/A= .06877 RATED SHP= 474.0
DEW PT.~ 42.0 REL.~UMIQITY= 14.0 PERCENT SPECIfIC HU~lDITY=
- GND IDLE FLT IDLE
POWER - SE-TTING NUMBER 1 2 6-
PERCErH '~A". CORRECTED POWER 0.0 0.0 15.1
CORRECTED SHAFT r-IP 0.0 0.0 71.7
MEASURED SHlIFT "IP 0.0 0.0 71.7
EXHAUST GAS TEMP., UEG.f 910.0 935.0 995.0
SHAfT SPEED, Nl, RPM 3?001.0 37746.n 41936.0
SHAFT SPEED, N2, RPM 31052.0 449A2.0 45004.0
COMPRESSOR INLET TE~P.,OEG.F 10~.0 109.0 109.0
COMPRESSOR DSCHG. PRES..PSIA 34.9 47.4. 60.5
COMPRESSOR MAP fLO~,LB/SEC 1.61 ~.20 2.72
FA RATIO dASED ON ~AP FLOW .0130' .01~q .0141
CORRECTEn FUEL fLOW, Le/HR 68.5 93.5 125.6
FA RATIO CALC. FRO~ EMISSION .0122 .0123 .0136
EQUIVALENCE RATIO .177 0178 .198-
oo*o*****ooo*****oooooooooo**ooooooo*oooo*oooooo*oSUMMARY OF
CAR80NDIOXIDE - --
")
S/'\i
- -)
t)
:')
(
1
;)
i
')
. "
) -
PERCE~T 8Y VOLUME
LB. C02 PER L~.Of fUEL
w~IGHT FLOW, L8./HR.
2.46
- 3011
213.1
2.79
3.15
39~.0
2.50
- 3014-
~93.9
1'tI~""""
. PI 06' ~ CAReON MONOX IDE - --
- ''-'I '0 I-
>(1) CD 00
IN 5.~-
I ~."t
I txI~
- UN8~RN€U HYOROCARBO~S- AS PP~ CARPON
PPM BY VOLUt-'€
LB. PER 1000 LR. OF fUEL
~iE IGHT FLOW, LA./HR.
,
- 345.0
";!7.758
-1.903
161.0
--1~.874
- 1.204
104.1
7.485
- .940
. - - - . ---'
:)- PPM BY VOLUME
t. - LB. PER 1000 L8~ OF fUEL
- wE1GHT fLOW, LR./HR.
,;)--- --NITRICOXIOE- ----- --- ---- _n -
99.0
4~555 -
.312
11.8
- - .483
.061
21.5
.9B4
.092
11
33.2
157.4
157.8
1070.0
45065.0
451)11.0
111.0
72.5
3013
.0160
164.4
.0149
.217
REDUCED
- 3.05
3.16
51<1.1
75.7
4.984
.819
-~- - ~- u .
RATED EGT=1090.0 DEG.F RATED SPEED= 51000.0
.00589 BAROMETRIC pQESSURE=28.60 IN HGA
16 20
44.2- 54.1
209.'5 256.3
210.2 -257.9
1100.0 1120.0
46517.0 47423.0
44961.0 44946.0-
112.0 115.0
78.9 85.3
3.35 3.52--
-.0170 .0177
186.5- 203.5
.0159 .0116-
.231 .256 -
EMISSI0N_DATAOO~00000*0*~00oo~*00ooooooooooooo~00o*0.0000000**0
3.25
3.16'---
589.2
3.59
3.16 -
643.0
-. --. --- -----
.. -'-- - -.-- -> --
---- - - '--' .._-----
- -. -. .
62.7
3.iH3
.722
61.4 -
--3.43'r - - -- ---- n-
.700 -
---- - --- ----- --" --
- ---'--.-
..----.-. -- _.._--~------ "----.
.----- -----
-- - .- . - - - --- - - -- ... -- - - - --
7.8
.294 --
.048
8.1
- .286
. .053
- -- - -..--
7.6
- - .242 --- --
.049
- --_._--- .'-- ----
.-..------- -----_._--------~--- ----
..... ---
---- ---
- ------ ._--'----'~- --
f) PPM BY VOLUME 16.8 31.0
- -- ------- -Lb~ PER 1000 La.-- OF -FUEL - -- -1.448 -- - 2.652
WEIGHT fLOw, LBo/HR. .699.248
- 55.1
,- 4.248
.534
:)---u n
NITROGEN DJOXIDE -
------
--- ---- .-- .._.- -- - -----.--- .
~) --_.:..
PPM 3Y VOLU~E 14.4
L~. PER 1000 L3~-OF FUEL ----1,905
wEIGHT fLOW, LB./HR. .131
11 ;5
1.513
.141
10.7
1.269 -
.159 .
:) ----
TOTAL O~IDES OF NITROGEN AS "102-- (3)-
83.0 103.0 122.7
5.859 - --6.~19 -'---7.358---~---
.963. - 1.272 1.497 -
.-- ------- --........-
---;----:'"1
--- -- -- -----
+ .---------- --------- ._-- "-----.---- -- --,--
- -
------_._~ -
8.8
.953 --
.157
8.7
- .887 .-
.165
12'~
- 1.158 ?---:----
.236 -
f
--_._------ ---
- --------
- ~--- -'-
-----------.------..------------'---"'--- ------ ---_._~-- -
--------- -~--------"--- -----
-~--,._---;
,)-- - -00000 NOTES 000** -- ----- ---- _h --------_..-- - -- --------,--- ---------______h_--_--____n___-_~--
I.ALL EMISSIO"lS CONCE~TRATInNS CORRECTED TO CONCENTRATION IN WET EXHAUST FROM COMBUSTIoN WITH DRY AIR.
J---- ------ 2.EQUIVALENCE RATIO CALCULATED FROM C02,CO,- AND HC DATA AND ~UEL COMPOSITION. --
3.TOTAL NITR'OGEN OXIDES CALCULATED USING NOX CONCENTRATION AND MOLECUL4R WEIG"1T OF N02- (46.0U..-------:------------
:. -)-
31.2 42.5
4~124 - _m 5.580
.283 .522
- 65.9
7..782 -
.977
PPM BY vOI.UME
La. PER lo06-L3. OF FUEL
wEIGHT fLOw, L~./HR.
91.8
- q.935 .
1.634
111.7 135.3
11.342 - - - 12.439
2.116 2.531
----------- ~--~-_._.
..--.------,----.------- --
- -
----. - .---
----.. -- ----
------.-.- -- ----~-_._---_._--- - - -- - - - --- - - --- --- - - --- -- ---_._- --- --- 'T ~ ...-,.-----:-------------..."...-----~....,...- -------.-
-------
(
--.-
- ENGINE TPE331-151G
(..r
....- --FUEl-H/C=I.928 ---
DEW PT.= 25.0
C- 0
- ~
; ;--~
Lo
PERCENT 8Y VOLU~E
LB. C02 PER LB. OF FUEL
--- ---:-- WEIGHT" fLOW, la.-/HR. - -
EPA-AIRESEARCH EMISSION PROGRAM TEST SUMMARY
---0-000000000000*000001111 0 II 0 00 OiHHI 0 0 0004141 0 0 0110011110
TYPE OF ~UEl
SIN ' P-91165-
DATE Of TEST
1.14 1.44 2.06
2.99 :3.07 3.13
224.4 - -- 4?O.8 --- "62~.r-
\if ~ CAR_S::M M::O::~~:E.._n ------~ '-~-~-7 :~--- ~~-;4 ;~3
= ~I -
(IN P, ~I - LB. PER 100. OL"!. OF FUEL 42.561 33.663
~'I' - ... IoJEIGHr FLOW, L8./HR. - - -'3.193 - - 4.612
~I - - - - - - -
C --,~::_L--U~BU~~ED- HYDR.9c.~~80NS: _AS ~-"'M__~~qON- -,-...-- -- - .-- --..-
STOICHIOMETRIC 'F/A= - .06843 "---, RATEDSHP= 665.0 u RATEDEGT=1060.IJ DEG.F RATED SPEED= 41730.0
REl.HUMIDITY= 10.0 PERCENT ,- SPECIFIC HU~IDITY= - .00285 GAROMETRIC PRESSUR~;28.67 IN HGA
'- - GND IDLE FLT IDLE
~OWER--SETTING NUMBER - -- -- -.. - - -, 1 2 --n_.- -- --6-
PERCENT MAX. COR~ECTED POWER.2 .5 26.1
. i ( CORRECTEO SHAfT HP - 1.0 3.~ 173.4
---MEASURED SHAFT HP---- -- ------'-----r~-o 3.1----- 111-.4"
EXHAUST GAS TEMP., OEG.f . 135.0 515.0 700.0
( SHAFT SPEED, Nl, RPM - 27150.0 41000.0 41730.0
---COMPRESSOR INLET-TE~P.,DEG.F - -102.0 -- --92.0 -_u 92.0
. COMPRESSOR DSCHG. PRES.,PSIA -
( " COMPRESSOR ~AP FLO~'LB/SEC 2.52 6.06 6.12
--:---. FA RA-TIO BASED ON MAP FLO'''-' - . .0090 ...- .0068 - -.0098
COR~ECTED FUEL FLOW, L8/HR 15.0 137.~ 201.0
l FA RATIO CALC. FRO~ EMISSION .0089 - ,0072 .0101
-~-EQUIVALENCE RATIO - .----- --- -.130:- -.105- .148
- - ....*.....o..oo*.oooo.oooo..o*.....oooo*.ooo.o.*..SU~MARY OF
. (, __-.~R_?O~_~-~OX IE~ -----... _n_h - - ---- -----~-._-- -------- -- -
--. -..
( -,-_:"
,
- ':-'
(
C,-
~ (---
( ----
( ---
PPM BY vOlU'-IE
LB. PER 1000 LB. OF FUEL
WEIGHT FlO~~-L~./HR.
NITRIC OXIDE
PPM 8Y VOLU'IE
lB. PER 1000 LB. OF FUEL
-WEIGHT FLOW,- LB./HR. -
NITROGEN DIOXIDE
- - --- - - - -
PPM 8Y VOLUME
Ld. PER 1000 LA. OF FUEL
-WEIGHT'FlOw, LA./HR.
TOTAL OAIOES OF NITQOGE~ AS NOZ
- -- .--- -
PPM BY VOLUI-!E
£' LB. PER 1000 LB. OF FUEL'
'-'- '--- H --WEIGHT FLOW, LB./HR.
L-
(
549.3
34.(056
- 2.584
138.1
10.743
1.412
135.1 81.9 41.6 16.4
13.105 6. 333- 2.767 .953
2.634 1.678 .R49 .345
- -r -,.- - - .'. - -- ---. - - ------- - -+ .--.'.-.-- ---- -<.- ---
36.8 11.2 8.7 5.9
2.0:11 .496 .329 .197
.408 .131 .101 .011
- --_. .-..---
--. - - --
19-.1
1.'H7
.397
------ - ---'---- -- -
-- --- --.-
--- - ---
.----.,-.----.----
bll/?1
AV1A-KERO
3.1
.363
'.027
6.1
.886
.121
-----1 r - - -'-16
55.2 72.8
367-.4 - 483.9
-361.8 h 476.0
830.0 935.0
41730.0 41730.0
h '88.0- - -- ~- 81.0 .
- 20-
91.2 -,
605.9
596.6-\
1050.0
41730.0
- --- 88.0"-
~----_.- -~-.
- .- _.._-----~---
-. -----_..-
- -----
~-- ----------- -.-.---
. -
--- -- -.--
---------- ----.
--- ----- --_.---
-----_._-~
6.08 6.04 5.96
.0130- - - .0151 .0181
265.0 307~0 362.0
.0121 .0148 .01~0 -
,'.185- -- .216' --.248 - -- -------------. - _P__h- _...- --------
QED0CED EMISSION O~TA*II..IIO.O~OIl*OIlOO.OIlOIlO.II.O*II.oo.II.lIooo.o..o.....II. ~
- -~ --'-'---
- - - ------ -- --~ -,-- --
-- - -- -----
- 0
~--...-- - -------.---- - -------- --~- ---.-
- ._-----~_J
-'~-..'--~---------.- -------~. ---.
2.59
3.14
-83?.8
3.02 3.45
3.15 3, 15
966.1- -h-114~.O
- - - ~ - ---- ~ - . --- -- --- - ~ --
----,-- ---.,
-~----- -
-. -- ~--
.----- ._--~---
. -.- ----~~
)
- --- --- - ~----_._--
-~- -----------. --- .-.--
- -
- - ----- - -- . ,-.J
------ - -..
- -->------..
- -.--.-.- --
- -----
- -~_._.
32.7
- 2.111
- .719
47.8
3.404
1.045
62.0 -
3.857
1.396
-~. -- -- -- --.-
1'U 13.8 13.1 9.1 6.3 4.5
1.423? 3.093 2.073 1.161 .691 .431 :i
.107 .424 .411 ~308 .212 - - .156
(31 -
--- --- _._~- - - - - - -, -.- -. -- --~.
11'.0 19.9 32.2 41.9 54.2 66.5
1 . ~79 4.452 5.104 5.318 5.910 6.345
.148 -- .610 1.026 1.409 1.'J14 2.297
0.... NOTES .....
- 1.ALL EMISSIONS CONCENT~ATInNS CORRECTED TO CONCENT~ATIQ~ IN WET EXHAUST FROM COMBUSTION WITH ORY AIR!
2.EQUIVALENCE RATIO CALCULATED FROM C02,CO, ~ND HC OATA ANO FUEL COMPOSITION. -
3.TOTAL NIT~OGEN 0~IDES CAlCUL~TED USING NOX CONCENTRATION AND MOLECULA~ WEIG~T OF N02 (46.01).
-------
-...,
-,
")
t)
")
-'I
)
I.,,;:. G"J
I II> 'tS ~ '
'\Q'tS I
'!P(I)CXI
i~[~
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,~ I
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I, ' -
ENGINE
TPE331-1S1G
SIN
pen 168
FUEL H/C=I.928
DEW PT.= 25.0
,
PERCE~T BY VOLUME
LB. C02 PER LB. OF ~UEL
WEIGHT FLOw. LB~/HR~
I.6Z
,2.90
223.3
CARBOI~ I~ONOX I DE
-...... _.- - .. -- --..
- - -- - -- .-- --~ ~ ~
PPM BY VOLUI4E
L~. PER 1000 L~. OF FUEL
WEIGHT FLO~, L~./HR.'
380.8
43.324
3.336
UN8URNED HYOROCAH80NS AS PPN CARRON
, , ,
~,":' -<~,--;---:-, -::.-ti~=;'r~';-v15L U'JE
l~. PER 1000 LB. OF FUEL
WEIG~T FLO~. LQ./HR.
1037.4
67.464
5. 195
,/--__~!TRJ~--~~!~E______-------,--- , --
'PPM 3'( VOLU'~E
SJ--- "__H LB. PER 1000 LB. OF FUEL
WEIGHTFLO~,LB./HR.' -
- - - -- --
4.4
.5.33
-.041-
. ' .
;)____N_I_T~OGE~_O_!O)(_IDE -_u -- ----
PPM BY VOLUME ,
lB. PE~ 1000 Lq. OF FUEL
wEIGHT FLOw, LB./HR. '
). _.
---..------ .- - -
. ,12.2
2.289
.. .176
)._--- !~~~l__O_X~~~.~ OF__NI_!~_I DIOXIDE
- -. -.- --
"---- - ---~-
--- .- ------ ---
50.0
3.195
1.013--~
34.8
1.916
.107
--.--- --- -- -
------ - -~-
---~._-
--- -- ~ ------
-- - -- -----. - -- -"--
- - - --J
u_-- - ---- -----
- ---- ------- - -
3.0
.111 .
. .; 035
1.3.
.040
. .015
-. --~ - -
-- -------
-- ----.--._- ----"
-- -.-----------------
- -~ - ------- ------ ---
----------- --- - ~----- ------ - -
88.3
tJ.n46
1.917'.-
111.8
6.593 '
2.'433n~---'---- -------.---'---
- ------ --
--- - ---'--,
, ,
-- - ---. -~---------------------~---_._--.-
---- -~--
_.~ ----
-- - -- -
, 10.8 7.4
1.133 . .670 , .
.359 - --- --.24 7 ---~ --.n - --___n- -----:-w ---
..-- ------------ -
--------- -----
- _._---~-----
--------~--.
---- -- -- ---------------- -
52.0
9.075
1~791
99.1 119.2
10.403 10.718
3.298 n- - 3.-977
-- ----------------- ---_._----~ - ----_.~
)- ---_u 00000 NOTES 000.. ,
I.ALL E:rIISSIO~IS CONCENTKATIONS CORRECTED TO CONCENTRATION IN WET EXHAUST FROM COMBUSTION WITH DRY AIR!----------
2.EQUIVALE\CE ~ATIO CALCULATED FRON C02,CO, AND HC DATA AND FUEL COMPOSITION.
J-___n__. 3.TOTAL NITqOGEN OXIDES CALCULATED USING NOX CONCENTRATION AND f.10lECULIIR WEIGHT OF NOZ 146.01)..
---- -- - -- -- -----.--- _._- ----- ----- -. -. --
-------
c ~~-- -c-----------~~~~;::;:;~;;;~~~~1t;~;;;;~~1I::2~~:~1I~;;~1t;~~~:~~ --,-- , -, - --..----,___,_h__-__-
,ENGINE TPE331-43A SIN P-61157 DATE OF TEST 5/11/?1 TYPE OF FUEL JP5
C::::~-FU'EL-H/C=1.877-- ~STOICHIOMETRIC F/A='-.06817 -- RAT~D SHP= 575.0 -~ RATED EGT=1060.0 DEG.F - RATED SPEED= 41730.0
'. DEW PT.= 35.0 . REL.HUMIDITY= 1&.0 PERCENT SPECIFIC HU~IDITY=.00441 8AROMETRIC ~RESSURE~28.76 IN HG~
. ( , . GND IDLE FLT IDLE
----:-~'-POWER-SETTING NUMBER 1 - 2 ---. , 6 .._, 11 .._-- -16 - -20 n~__'- ___"un - -- ,- -,- -- ---- - ---- --- .
. PERCENT MAX. CORRECTEO POWER .5 1.1 24.5 4&.8 ' &9.2 87.6
C CORRECTED SHAFT HP '2.7. 6.4 141.1 269.4 397.7 503.5
. -:-----MEASUREDSHAFT HP _n' '''--Z.7---'-- -6.3 - 139.6- 266.6- -- -393.5 498.2
EXHAUST GAS TEMP.. DEG.F 615.0 620.4 745~0 860.0 975.0 1090.0
SHAFT SPEED. Nl. .RPM' 35535.0, 41730"0 - 41130.0 41730.,0. 41730.0 41730.0
COMPRESSOR INLET 'TEMP.,nEG.F--' - 96.0-'- 88.0:-'- '-90.0-'" 90.0--- -.- 90.0-- _n. 90.0"---.
COMPRESSOR DSCHG.PRES.,PSIA .6b.4 '95.4 98.9 102.1 104.3 106.0
( . CORRECTED FUEL FLO~ , LR/HR 101.0 150.0 197.0 246.0 293.0 338.0.
---'-FA RA'TIO CALC. FRO"1 EMISSION :.0078' ... ~.0079- --.0104 ;0127 - .0143' -- .0166 - _.__u_-----------,- -----
EQUIVALENCE RATIO, .113 .115 .152 .1804 .208 - .241 . .
( -----' ~:~:~~I1~;~:;~;IIII~*IIIIII~~II_II~~OII_~,O~~II~,II_OII~ ~~~,~IIII_II~II- SU_~MARY OF - REDUCED EM I SS I- O~ ~~ T A 1t_~~IIII~~~IIII,~II~IIII~~~~~,~~~~:IIII,II~II~~_lIIIttlllIIIlI~O"'~~~~~~IIO
- (r " PERCENT BY VOLU;-1E 1.54
-'------1:.8.- C02'PERLB~-OF 'FUEL' - - -. 3'-04
. . WEIGHT FLO~~ LB./HR. 306.7
C-i~fifUCARBONI'IONOXIDE " - .. ,_c.._-, ,--
IQ '0 I '
«D ~ ~ - ,- ,PPl'i8Y VOLUME " 289.6
UI p,.... Ld. PER 1000 LB. OF FUEL. 36.23& .
'~:~ WEIGHT FLOW. LB./HR. ',3.660'
(~. .' '
,~L UNBURNED HYDROC4RBONS AS PP~ C~q~ON -
L
~. ..~
l,">:'" .
-+:-- ._~- --
PPM BY vOLU~~E
'LB. PER 1000 LB. OF FUEL
WEIGHT FLOW, LB./HR.
'(
.---NITRIC' 'O)(IOE
'( . PPM BY VOLUME
. -------, .----LB. ptR-I000 LB. OF FUEL
wEIGHT FLOW, LB./HR.
c.~-
, NITROGEN DIOXIDE'
( -------
PPr-1 BY VOLUME
-- LB~ PER 1000 LB. OF FUEL
WEIGHT FLOW. LB./HR.
(o.
'TOTALOXIiJES OF NITROGE'J AS ~j02
( PPM BY VOLUME
- -- -- --LB. 'PER 1000 'LB. OF FUEL
WEIGHT FLOW. L8./HR.
/
~--
1.62
- - .., 3.14
470.5
2.14
-3.15'"
61'!.7
Z.60
3.16 .,
.776.6
- -- -- ---- -------- .
70.5
5';450
1.341
- -.. - H - - - - .- - --- - .
2.93
3.16 _m
926.6
.-. .- --_._-
... - .- - -----_.~ . -..-------- - - .
-------
---- - .--- .n_-
.- -- -----_._-
369.0 24.5 12.0 2.7
;)6.392 . 1.727 .644 --. - .121
2.666 .259 .127 .030
..-- - - , .
4.6 21.3 31.8 69.7
.610. '2.818 3.792 5.772
.062 .423 .747 1.420
-----------_._- -
3.40
-3. 16
106'!.5
- - ------- -
--- -..- -- --.-
------- ___.0. -.-
- - ._------~-- ----, ---".
- -------+----_._------- -- -_'H-
----- -- ---
13.6
.806
.272
--- --. -.----. --
----- -- --- ---- ----
17.5.3 125.4
15.464 - '11.755
2.320 2.316
13.2
2.723
.275
25.5
3.923
.773
15.3
1.948
.479
85.0
10.797 . .
2.656
27.Z
'1.8&6 ..
.547
- ---- -- --
2.1
.082
.024
- - -- -. --- _. -
97.3'
7.160
2.098
8.0
.908
.2&6
105.3
11.884
3.482
---- ---------
-- ------
-.-- ---+------ -- .
- - --- - - -'-- ---.------+--
19.6
3.973
.596
(3) -
17.8
, 3.658
.369,
40.9
8.293 '
1.244
63.3
9.737
1.918
1.6
.053
.018
- -- - --- --.. ~--
----- - ------
- -. - - ----
- -- --- _. --- --
-- -- -+ - - +
119.1
7.570
2.559
- ---~-----+-
-- - - - - -- u--
- --------+
7.3
.712
.241
..----- ...----
---_.,-u --
-.- +-- ---- ----
126.4
lZ.318
4.163
<- -- -,
- - ***11* NOTES ***11*
I.ALL EMISSIO~S CO~CENTR~TI0NS CORRECTEO TO CO.~CENTRATIO~ IN WET EXHAUST FROM COMBUSTION WITH DRY AIR.
2.EQUIVALENCE RATIO CALCULATED FRO~' C02.CO, AND HC DATA AND FUEL COMPOSITION.
-------
")
. -,
)
"
)
)
')
}. ---
\
1:.6' ~
\Q '0 I
. (b (b CXI
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tJ7)j
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)-
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ENGINE
1;[00190
EP~-AIRES[ARCM EMISSIO~ PHOGRAM TEST SUMM~RY
0000000000000000000000000000000000000000000000
DATE OF TEST ~/bl?l TYPE OF ~UEL JP5
T7b-G-410
SIN
FUEL H/C=1.Q11
DEW pT.= 45.0
STOICHIO~ETRIC F/A= .06877 RATED' SHP= 720.0
'REL.HUMIDITY= 42.0 PERCENT SPECIFIC HU~IDITY=
GND IDLE FLT IDLE
1 2
.3 20.7
2.2 149.3
2.1 142.8
623.0 622.0
~7230.0 41730.0
61.0 59.0
6
41.0
295.4
282.4
708.0
41730.0
59.0
POWER SETTING NUMBER
PERCENT MAX. CORRECTED POWEH
CORRECTED SHAFT HP
MEASuRED SHAFT HP
EXHAUST GAS TEMP., OEG.F
SHAFT SPEED, N1. RPM
COMPRESSOR INLET TEMP..~EG.F
COMP~ESSOR OSC~G. PRES.,PSIA
COMPRESSOH ~AP FLOW,LB/SEC 2.68 6.50 0.47
FA RATIO BASED ON MAP FLOW .0077 .0086 .0107
CORRECTED FUEL fLOW, LB/HR 71.0 lQ2.0 238.0
FA RATIO CALC. FROM EMISSION .0083 .0092 .0112
EQUIVALEI\jCE RATIO .121 .133 .163
ooooooooooOooooooooooooooo*oo**o*oooooooooooooOOOOSUMMARY OF
CARSON UIO)(IDE
PERCENT 8Y VOLUME
Ld. C02 PER LB. OF FUEL
wEIGHT FLOW, LB./HR.
1.61
2.97
211.0
1.86
3.11
597.7
CARBON ~1Oil/OX IDE
. - .--.-----
- - -- -- '- . -
PPM BY :VOLUME
LB. PER; 1000 LB. Of FUEL
wEIGHT FLO~, L~./HR.
482.2
56.740
4.029
223..0
23.795
4.567
UNBUR~EO HYDROCAR80NS AS PPM CAQBON
. - - -- .-___~n-
- - -. - .-
PPM BYVOLU'1€
"Ld. PER 100Q L8. OF fUEL
- wE I GHT "FLOW,: L8 oIHR.
564.1
37.939
2.694
91.4
5.575
1.070
NITRIC OXIDE
--------
- -- --. ---_._--- - -- -
- --- --- -. -
- -_.- ------
PPt-l BY vOLUt~E
L8. peR 1000 La. OF FUEL
-~~IGHT FLO~, LB./HR.
. ~
NITROGEN DIOXIDE
-. - - - ~'. +- .
1.9
.240
-. .017
12.-6
1.444
.277
~---_. .__. -.
-------- - - -- - - ----- -
PPr-I B:Y VOLUME .
La. PER 1000 LB. Of FUEL
w£IG~H FLOW, La./HR. -
12.1
2.331
.166
. 29.3
5.137
.986 ..
) TOTAL OAIOES Of NITROGEN AS N02 131 .
------------ -------:------ -_..-------- --. .'----.---______0..___----"---
PPM 8"( VOLUME 14.0 42.0
LB. PER lQOO L~. OF FUEL 2.698 .7.351
WEIGHT FLOW, LI3./HR. '. - - .192 "1 ~411
, "-
J-- .
2.29
3013
145.9
11
62.7
4S1.~
431.6
815.0
'41730.0
. 59.0
6.45
.0132
293.0
.0130
.189
REDUCED
2.65
3.15
922.0
RATED EGT=1060.0 DEG.F RATED SPEED= 41730.0
.00661 BA~O'1ETRIC PRESSURE=28.61 IN HGA
16
83.0
597.4
571.2
930.0
41730.0
59.0
20
96.8
696.9
6b6.4
1010.0
41730.0
59.0
6.38 6.33
.0158 .0178-
347.0 387.0
.0151 .0168
.220 .244
EMISSION DATA*O~oooooooooo~o*oooooo~oo~oooo*oo*oooo*oooo****..*
3.09
3.16
1095.2
.--- - -. -- ---.--.- +-
190.2
16.571
3.944
39.9
1.987
. .413
.----.--"
27.5
2.566
.611
------ -
29.3
. 4.200
1.000
- ~- -----
56.8
8.133
1 .936 -
. 151.5
11.432
3.349
-----. ." --
9.2
. .396
.116
. 91.1
5.928
2.057 --
. - ---- --- -~._-
2.2
.083
.029
-- - . -".
3.44
3.16
1223.1.
.~ --"-- - -~-
--- ----.- ---- ..0.-
.-. - ...- -~- - ----- '--
, - ..----- -- ._--.-------'--
. 38.9
2.280
.882 :----
- - --- - - ----_.- ..-
-'-'-- -- .-.---
. ._~--- --
~-'- -- ---.-
- ---..-
--.-- -- .-.--
1.4
.048
- - .019
-"-'----. -- --- -- -~
.-.- - -- ---- .--- ---
- - - ---- --.
. .
_._- ._~ ----.--------- --- ---_._-_._--------~----_. -- -
~-----. --~--.....
- - .--..--- .---- ---- .-.
50.7
4.099
1.201
80.8
5.630
1.'954 _.
--------- -------
22.1 11.7
2.745 1.251
.804' c -_.- .434
98.1
6.155 .
2.382'---C-----~~------' ----,_.
- - ----- .--- --- -
--- ~-~---------
-.' ---'.....-------. ~ --I
I
I
~ -~----_.-
.8.7
.839
-- -.325
--"--------.-.-.-- ~._-- ~~-----_._-------- --~
--~-- -----------.-- ._._._-------_._-~-
72.8 92.S
9.030 9.883
2.646-- 3.429 -
--------_. .--
106.8
10.27& .
~ 3.977--------
-------~--
) . ~o*oo NOTES 00000 . .
. - -- - - I.ALL EI41SSIO'IS CONCENTRATIONS CORRECTED TO COi-JCENTRATION.IN WET EXHAUST FROM COMBUSTION WITH ORY- AIR! ------'----
, 2.EQUIVALENCE RATIO CALCULATED FROM C02. CO, AND HC DATA AND fUEL COMPOSITION. . .. .
)-~-_u- _3_. TO~~~_~l.:r~OG~~_OXI~ES- C~~CUL~~E~_~~SIN~- _NOX- _C~~~_E~T~~~I?_~_~N~ ~~l.~CULAR WEIG_~T Of N02~~~~!~-
. ~
--. --_.~-<-----
-------
EB
AIRESEARCH MANUF'ACTU"ING COMPANY OF' ARIZONA
A DIVISIQN a,. THE QAIUII:TT CDRPORATIDN
GROUP 2
SMALL AUXILIARY
POWER UNITS
-------
(
. EPA-AlRESEARCH E~ISSION PROGRAM TEST SUMMARY
'---'____n__--- --~OiHIO~oooooooooooa'ooooOOOOO!lOOOOOOOOOO!looooooo -, ,- -
ENGINE GTCP30-92 SIN P-28194 DiTE OF T~ST 5/17/11 TYPE OF FUEL AV.KEROS.
c: .' (ATCMIZERS)
'----FUEI.:'H/C=1.928" STOICI1IOMETRICF/A= .06843 --
DEW PT.= 7.0 REL.HUMIDITY= 5.0 PERCEHT '
- --- ~.. ._-- --- -
--- ---_.._- -------------
--RATEDSHP='" 40.0
SPECIFIC HU~IDITY=
(-- SHP LOADING ONLY
-POWER SETTING NUMBER d. -1 ,- - - - ,,' 11
. PERCENT.~AX. CORRECTED POWER 0.0 25.8 51~3
, ( CORRECTED SHAFT HP - - --~--- 0.0 10.3 . 20.5
. ~'MEASUREOSHAFT HP--' '--O~O' 10.2- '---20.3- -
EXHAUST GAS TEMP.. DEG.F 64~.0 ~15.0 710.0
( , SHAFT SPEED. Nl. RPM , 59200.0 59200.ij 59100.0
----COMPRESSOR' INLEr TEMP~-.nEG~F h -. 83.0 .96.0---- - 100.0' -
, COMPRESSOR OSCHG. PRES..PSIA 39.3 39.3 39.4
( .' CORRECTED BLEED fLOw. LB/MIN 0.00 0.00 0.00
-- ---CORRECTED FUEL FLOW. L8/HR - 35.4' 31.4 - 40.4
FA RATIO CALC. FROM EMISSION .0086 .0093 ..0099
(_--__EQUIVALENCE RATlO .125 '.136..145
, ooooooooooooooooooooooooooooooooooooooooooooooOOOOSUMMARY OF
CAR80N OIOXIPE , . .
16--
77.2
30.9
30.5
745.0
59100.0
- 96.0
39.6
0.00 -
43~4 --
.0106
.154
REDUCED'
RATED EGT=1320.0 DEG.FRATED SPEEQ= 59000.0
.00117 BAROMETRIC PRESSURE=28.56 IN HGA
COMBINATION SHP/BLEED LOADING
- 20 22 19 15 10 5
102.8 102.5 76.8 51.3 25.6 0.0
41.1 41.0 30.7 20.510.3 0.0
40.7 40.6 ';'0.4 20.3 10;2- 0.0
795.0 1318.0 1320.0 1320.0 1320;0 1320.0
59100.0 58900.0 58900.0 59000.0 59000.0 59000.0
'98.0' '97.0 98.0 -- 99.0 '98;0 ~ ~ 98.0
39.7 37.0 36.4 35.8 35;1 .34.7
0.00 25.51 27.52 29.43 31.13 32.54
- 47!4 69.0 69!0 ' 67!5 65.5 64.0
.0114 .0201 .0199 .0198 .0195 .0191
.160 .294 ' .290 .289 .2!4 .280
EMISSIO~ DATAo~oo~~ooo~oooooooooo~ooooooooooooo~ooooooooooooooo
C -- - . PERCENT 8Y VOLUME - ,- -- u r. 72 - -. u - 1'-88 --~-'2.02 ~--~-2.32 4.07 ' - -4.02-- -4.00 3.94 3.88
2.15
. .i LB. C02 PER L8. OF FUEL 3.09 3.11 3.12 3.12 3.13 3.15 3014 3.15 3014 3.14
~ Co WEIGHT FLOW, LB./HR. 109.2 110.~ 125.9 135.6 148.4 211.0 2i7.0 212.3 205.9 201.2
-- ---- ---- ..- - ----- -~ ---- -- "-.- ------->-- -- - --- ~-- - - - .~ - - -- - -- --
-;;;-~C') I CARBON MOI~OX IDE
( 11/ 'tI >-31 . ' -
~ 'g J:, I - PPM ~y VOLUME . . - '331.4 26603' -. 224.5 193'-0 170.3 107.0 111.5 111.5 121.3 123.9
~&~ La. PER 1000 LB. OF FUEL 37.788 27.997 22.091 17.874 14.637 5.259 5.549 5.576 6.159 6.394
( '~.~I' ,. WEIGH.T,FLOW. LB./HR. ---'-- 1.338 1. 047 .892 .776 .694 .363 !.38j .376 .403 .409
-. - --- -. --:- 'I
-~~ UNBURNED rlYDROCAR80NS AS PPM CARQON
(.-;_. ---..-- 'PPM"SY vOLU..-4E 52.6' 24.5 13.5 09.1 6.6 4.9' 4.9 3.8 3.5 3.2
LB. PER 1001) L". OF FUEL 3.428 1.472 .761 ,.512 .326 .139 .139 .110 .103 .094
C WEIGHT FLO\~. Le./HR. .121 .055 .031 .022 .01.5 .010 !.010 .007 .007 .006
--_.
NITRIC OXIDE
( '~-." - PPM BY --vOLUME 7.7 -.. - .- -- 9.2 11.3 16.3 41.A 40.4 39.2 37.6 36.0
14.0
LB. PER 1000 LB. OF. FUEL .936 1.038 1.19" 1.392 1.500 2.201 2.156 2.102 2.046 1.989
( ~--, WEIGHT FLOw. L8./rlR. .033 .03~ .048 .060 .071 0152 !14~ .142 .1~4 .127
-' - - _-n- ~
NITROGEN DIOXIDE
(-- --- -. PP"I BY VOLUME 5.1 5.1 5.0 5.2 5.3 4.1 3.9 3.5 3.7 4.3
La. PER 1000 L3. OF FUEL .948 .8A3 .802 .785 .750 .332 .315 .284 .309 .365
, (-- WEIJ3HT FLOW. LQ./HR. .034 .033 .032 .034 .036 .023 !022 .019 .020 .023 - j
-.
TOT ALO,q/?E,S Of NITROGEN AS N02 (31
c--- -, - PPM BY' VOLU~1E 12~7 14.3 16.3 19.2 21.6 45.9 44.3 42.1 41.3 40.3
LB. PER 1000 LB. OF FUEL 2.383 2.475 2.632 2.919 3.049 3.106 3.620 3.506 3.446 3.415
(:. WEIGHT FLOW. L3./HR' ..084 .093 .106 .127 .145 .256 !250 .237 .226 .219
.00110 NOTES *11000
c- I.ALL PIISSIO'JS CO~CENT~A TI nlJS COR~ECTEO TI) CONCE~HRATIO\J IN wET EXHAUST F~OM COMBuST! ON WITH DRY AIR.
2.EQUIIIALENCE RATI') CALCULATED FRO"C02.CO. AND HC DAT4 4'40 FUEL C/JMPOSITIOIII.
3.TOTAL NIHOGEN OXIuE5 CALCULATED USI'IIG NOX CONCENTRArI:JN AND MOLECUL<\~ WEIGHT OF N02 146.011.
-------
EPA-AIR(SEARCH E~ISSI~~ P~OGRA~ TEST SU~MARY
~~~*~~~~~ooo~ooooooo~ooo~ooooooo~~~~~oooooo~oo
}
51-18/71
TYPE or FUEL AV.KtROS.
RATED EGT=1320.0'OEG.F RAfEO SPEEO= 59000.0
.00202 BAROMETRIC PR(SSURE=28.84 IN HGA
COMBINATION SHP/BLEED LOADING
20 22 19 15 10 5
102.4 101.7 ~6.2 50.6 25.3 0.0
40.9 40.7 30.5 20.2 10.1 0.0
4~.640.3 ~0.3 20.2 10;1 0.0
B5~.0 1315.0 1320.0 1320.0 1335;0 1330.0
58900.0 58600~O 5P609.0 58600.0 58600;0 58600.0
88.0 89.0 91.0 95.0 96.0 95.0
40.5 38.3 37.4 36.5 35.1 35.1
0.00 20.07 24.0027.39 30.95 ,32.82
50.3 68.0 68.0 67.0 67.0, 66.0
.0109 - .0157 .0159 .0171 .0171 .0119
.159 .229 "232, .249 .258 .261
EMISSI0~ OATAooooooooooooo~o~oooooo~~~~oooo*ooooooooooooooooo..
OIlTE OF TE.5T
ENGINE GTCP30-92 S/:J P-2!H94
(VAPORIZERS)
_FUEL H/C=1.928 5TOIC~IOHETRIC F/A= .06843
DEW PT.= 18.0 REL.HUMlnITY= 15.0 PERCENT
'"
RATED SHP= 4~.0
SPECIFIC HUMIDITY=
SHP LOADING ONLY
POWER SETTING NUMBER 1 6 11
PERCENT ~AX. CORRECTED POwER 0.0 25.8 51.6
CORRECTED S~AFT HP 0.0 10.3 20.6
MEASUREiJ SHAFT HP 0.0 10.2 20.4
EXHAUST GAS TEMP.. DEG.F 610.0 650.0 695.0
SHAFT S~EEO. Nl, RP~ 5Q200.0 59200.' 59200.0
CO~PRESSOR INLET TEMP..~EG.F 82.0 85.0 85.0
COMPRESSO~ OSCHG. PRES..PSIA 40.2 40.2 40.3
CO~R[CTED 8LEED FLOW. L~/Ml~ 0.00 0.00 0.00
CORRECTED FUEL FLOW, LB/HR 36.4 39.4 42.4
FA RATIO CALC. FRO~ EMISSION .0086 .0094 .0099
£QUIV~LENCE RATIO .125 .137 .145
ooo~~wo~o*o**oo~****o***o*o~*oo*~*****o*~*~*o**o**SuMMARY O.
CARBON DIOXIDE
')
1/'..
77.2
30.9
311.5
765.0
59000.0
83.0
40.5
0.00
46.4
.0103
.150
REDUCED
: ')
, ')
! )
"
, }. - ---
PERCErH BY IIOLU"1E i.74 1.90 2.01 2.08 2.20 3.17 3.21 3.44 3.56 3.60
La. C02 PER LB. Of FUEL 3.11 3.11, 3.11 3.11 3.11 3.12 3.12 3.12 ,3.12 ' 3.12
WEIGHt FLOw, LB./HR. 113.7. 122.6 13!.9 144.2 156.2 212.2 21':.2 209.2 20?3 ' 206.2
CAR80N MONoxIDE
PPM BY' VOLUr~E 234.5 257.1 271.4 309.5 332.8 . 341 .2 --, 345.4 -- 342.3 346.8 341.1
Li:>. PER 1000 LB. OF FurL ::>6.657 21',.759 26.750 29.4R2 29.876 21.380 21.366 19.773 19.349 18.831
WdGHT FLOw. LQ./HR. .970 1.054 1.134 1.368 1 . 50,3 1.454 1~453 1;325 1.296 1.24~
UN~iURI\;EO HYDROCARBONS AS PPM CAR~ON
')
'1:I;I>oc:l
IU 'tI ~
-'\Q'tI1
(I) (I) co
::!..,j
coo..c.
""..,j
)C I -
b:I::a
. '-------
, ") ---
1.0.
;.032 .
.002
7.3 5.3 5.6 7.1 6.5 ' 3'.1 - 2.6 - 1.8 .. 1.5-
.475 .312 .315 .384 0336 .110 .091 .060 .048
.017 .012 .013 .0'}8 .011 .008 ~006 .004 .003
12.0 13.1 14~0 - 15.9 ' V,. 6 28.9 29.5 31.6 34.5 ~
1.460' 1.4{,6 1.483 1.623 1.597 1.943 1.958 1.953 2.060
.053 .058 .063 .075 .080 .132 !,133 .131 .138'
PPr-I BY vOLUr~E
L~. PER 1000 LB. OF FUEL
wEIGHT FLOW. LB./HR.
J---
+-,
I
NITRIC 0)(10E
~ )- ----'
- U -- PPM 81110LUME
Lu. PER 1000 LB. OF FUEL
WEIGHT FLOw, Lq./HR. .
35..3: - '
2.086
-- -- _.138 ~-~.
):"'_--- ,
-- - -- - -'.
NITROGEN DIOXIDE
J-----
9.4
, .851
.056,
9.3
.851
, ~ 0!)7
8.9
.847
.057
9~9
1.017
.069
9.2
.933
- !,063
'9.6
1.420
.071
7;"
1.304
.051
8.0
1.300
.055
PPM BY - vOLUr-1E -
LB. PER 1000 LB. OF FIJEL
wEIGHT FLOW. LB./HR.
- - -- . - - - - - ---
8.6
1.350
.063
7.2
1.349
.049
) - ------ ,
- -- --- ----
TOTAL OAIDES OF NITROGEN AS N02 (3)
) ------- - _u --- - -- ,- - ---- --_: - -
PPM BY VOLUME 19. Z
LB. PER 1000LS. OF FUEL 3.587
= )------__WE!GHT- fLC?V(. _LB!'):!R--- ------- _.131
-- 38~8 -- --~38.7 -- --- 40;5---~. 43~7-----'.44'-7 -~-
3.996 3.935 3~842 4.009 4.049
-~. !2.!2 ---- _~~68- ___~,25!___-- ._z..,,~-_____,-2_~!__-
---20;8- - ----22~1----- -24.5 - - - 26.2-
3.551 3.574 3.839 3.869
- -- __._1_4"Q,_____! 152 ._17.!.-___- ..195
oo~*o NOTES 0*000
I. ALL EMISSIONS CO~CE~TRATIONS CORRECTED TO CONCENTRATI0~ IN WET EXHAUST FRO~ COMBUSTION WITH DRY AIR. ,
c.EQUIVALENCE RATIO CALCUL/ITEO FROt-! C02,CO.. AND HC DATA AND FUEL CO'~POSITION. -,' - - -- - -- -- - --n -~----
3.TOHL NITROGEN OXIDES CALCULATED uSIf\iG'.NG'X C-ONCENTRATION AND MOLECUI.AR 'WEIGI"4T OF "102 146.0q.
)-- --
---~- --
- --~. -----
-------
(
: EPA-~IRESEARCH EMISSION ~ROGRAM TEST SUM~ARY
-~-~-- ,+000000:0 CI 0 0 0 00 011 CI 0 0 011 CI 0110 011* 011110110* * 00 0 0 0 0 OClCl 0
JP5
DATE OF _TEST
(---~------PER-CEI'ojT--BY'IiOLlJME ---- - - - - -- -1-;52 -- -:"-- f~96
- Lti. C02 PER LB. OF FUEL 3.13; 3.13
WEIGHT FLOW, L9./HR~ 202.1 213.8
..---------. _.-- -- ..-- ---_._- - -- - --._---.- ---- --- -
- ENGINE GTCP36-6 SIN P-34696
-r ' - -
-('----FUEL-H/C=1.87T-.---STOICHIO,~ETRIC F/A= --.06877- RATED SHP=- 160.0 '-RATED EG'=1200.0 DEG.F RA!EO SPEED= 58608.0
OE~'PT.= 36.0 REL.HUMIDITY= 14.0 PERcE~T- SPECIFIC HU~IDITY= .0~502BAROMETRIC PRESSURE=28.65 IN MGA
( ----- - ' ~- SHP LOADING ONLY COMBINATION SHP/BLEED LOADING -
- POWER SETTING NUMBER 1 - 6-- ,- ---11 15 10 5--- --- ----- --- ------------
PERCENT ~AX. CORRECTED POWER 0.0 25.8, 33.8 57.2 25.5 0.0
'( - CORRECTED SHAFT HP - 0.0 41.3' 54.1 91.6 40.8 0.0'
------MEASUREO'SHAF'T Hp. - ------- ---:--0;0----"--4l.()--:- -53.7 91.1 - 40.6 0.0-.-
EXHAUST GAS TEMP.. DEG.F 600.0 i15.0 750.0 -1200.0 11~5.0 1175.~
I ( SHAFT SPEED, N1, RP~. - 59200.0 59100.0 59000.0 58400.0 58600.0 56BQO~0
----COHPRESSOR INl.ET TEMP'-,fJEG.F ---- - 98.0 - ',-98.0 - 98.0 100.0 - 101.0 102.0'
COMPRESSOR DSCHr,. PRES..PSIA 53.0 153.2, 53.2 50.1 47.0 44.3
(' - CORRECTED 8LEED fLOW. L8/MIN 0.00, - 0.00, 0.00 42.35 59.04 81.70
-----:---CORRECTED FUEL FLOW ,- La/HR 64~5--m 68.3" 94.-i 149.4- ---137.0-- -- 123.9
FA RATIO CALC. FROI-l EMISSION .0074 -.0096 .0104 .0187 .01--76 .0180
( EQUIVALENCE RATIO - .108, .140 .151 .271 - .257 .262
- ~--- OOO*O*O***CI*O*****CI****CI**CI*~ClCI***O***OClClO~ClClO*OO*SUM~1ARY OF ~EDUCED EMISSION DATAIiOClO*OIlClO**OOOO*OOOO*II**OO*O*OOOOOO**ClOO**OOOCl~IIClO
CARBO~ DIO~IDE . ,-
---2'~ 12
3.13
294.6
(.~
~~-;l CARSON MONO~IOE
4J;:g'f!
CD CD (XI I PPM -BY vOLU~E 1"45.6 --- -- 21)6.; . - -, 218.8
~[~: LB. PER 1000 LB. OF fUEL 19.069 20.957 20.573
,4 ~.I':.._-- WEIGbtT FLOW, L8./H~. ------ _--1_.230 '1._~3Lu_--__l.935
~: -
- ~ ; UNBURNED HYDROCARBONS AS PPM CARqON
(:------:------- PPM -ay ilOLU'-IE - - -- - _u- --14~2
- LB. PER 1000 LB. OF FUEL 1.064
(~ - - - _u'- ~~~,I3HT- FLOW. LB ./H_'3' - .069
NITRIC OXIDE
( ---
- PPM -BY VOLUME- -- -
LB. PER 1000 LB. OF FUEL
WEIG~T FLO~. -LB./HR.
( ---
(- ----
NITROGEN DIO~IDE
PPM - RY VOLU,-IE
LB. PER 1000 LB. OF FUEL
- \liE IG~TfLO\ll '__!-8 ./HR.
( ----
11.3 ---1"8'-9' 20.2 - 47.5 40.9 41.3
1.~91 2.055 2.036 2.689 2.446 2.425
.103 .140 .192 .402 0335 .300
6.8 10.-3 12.1 12.2 13.4 12.6
1.455 1.715, 1.868 1.055 1.230 1.135
.094 .117 ' .176 .158 .169 .141
(3)
0- 15.2
.879
.060
TOTAL OXIDES OF NITROGEN AS ~02
(--,-u_-----PPM BY VOLU'1E ' -- -1801
LB. PER 1000 LB. OF FUEL' 3.B95
c:"" -_u'- - __W_EI_Gt:I!.fLOW, LR~iHR. .251
29.2
4.867
.332
14.6
.785
.074-
32.3
4.990
.469,
5/14i?1
3.79
3.15
4~9.9
243.3
12.857
1.921
3.9
.11~
.OI~
59~7
5.178
.774
TYPE OF ~UEL
.3;58 -
3.14 -
430.1
- 291.9
16.296
2.233
7.2
.230
.031
54.3
4.980
.682
.. -----
--- --_._------
---. ------
- ---.--
- --_._~----- --------------.
- ~ --- ------.-- -------~--------
- ~___.n__- --------~- .._--------------~-_.
.3.65
3.14
__nn ~~ ~-~-~
- - .- - _'0 -
.-- ...--.-- ------- ._---_~_--~_L~_. - _._- .
- ,
- - ------- _.. - ---
~ --" --- _.--
~~-_..-----_..-._-_._-- ~-
n 259.0
'14.193
1.758
---- -- - "----~~_.
.. - -- ----- -- -..- ~ -.- -.
- -. -.-- .-.-.-
----.--.--..--.- -"." -
9.0
.281
.035
- --' . .-----" .
. ------..------
_____L._..
-_. ---.--.--.---
-- .. --..-- '. -_u_-.
-. _._---------.-
-.- -"----- - - - -
__h .- -----
.._-----. - --
- 53.9
4.852
.601
--._---- -- -- -.-
- --. -_. -- -.--
(-- ---
00000 NOTES 00000 -
1.ALL EMISSIONS CONCENT~ATInNS CORRECTED TO CO~CENTRATIO~ IN WET EXH4U5T FROM COMBUSTION WITH DRY AIR.
-2.EQUIVA(ENCt, RATIO CALCUL4TED FRO~ C02.CO. AND HC DATA ANO FUEL COMPOSITION.
3.TOTAL NITROGEN QXIDES CALCULATED USING ~oXCONCENTRATtO~ 4ND MOLECULAR WEIG~T OF N02 (46.011.
-------
)
- .',
ENGINE
S/'IJ
P-34772
EP~-AIPESEARCH E~ISSION PROGK~~ TEST SUMMARY
**~~~~*~**~~*~oo**************~*~~oo*ooo~*oo**
OhTE OF TEST S/14/!1 TYPE OF ~UEL JP5
RATED SHP= 160.0
SPECIFIC ~U~IDITY=
SHP LOADING ONLY
POWER SETTING NUMBER 1 6 11
PERCENT MAX. CORRECTED POWER 0.0 25.1 49.9
CORRECTED SHAFT riP 0.040.2 79.8
MEASURED SHAFT HP 0.0 39.5 18.1
EXHAUST GAS TEMP.. DEG.F 540.0 ~3S.0 140.0
SHAFT SPEED, Nl, RPM 59100.0 58900.0 58600.0
COMPRESSOR INLET TEMP..OEG.F ~4.0 86.0 88.0
COMPRESSOR OSCHG. PRfS..PSIA 52.9 ~3.4 54.4
CORRECTED BLEED FLOW, Lrl/~IN 0.00 0.00 0.00
CORRECTED F~EL FLOW, LB/HA 12.6 90.6 109.6
FA RATIO CALC. FROM ElllSSION .0080 .0101 .0122
EQUIVALENCE RATIO .116 .146 .118
oo~*oo~*o****ooo**~oo*o***o*~oo**********~***o~o**SUMMARY OF
CAR80N (}IOXI0E
GTCP36-b
FUEL H/C=I.1'i77
DEw PT.= 37.0
STOICHIO~ETRIC F/A= .06877
REL.HUMIOITY= 17.0 PEPCENT
')
')
")
)
16
72.2
115.6
114.0
860.0
58500.0
89.0
54.4
O~OO
128.7
.0143
.208
~EDUCED
RATED EGT=1200.0 DEG.F RATED SPEED= 58608.0
.00481 qARO~ETRIC PRESSURE=2B.70 IN HGA
COMBINATION SHP/BLEED LOADING
20 15. 10 '. 5
75.1 49.3 24.7 0.0
120.2 78.9 39.5 0.0
118.7 78.~ J9.1 0.0
90~.0 1145.0 11~5.0 1155~0
58300.0 58200.0 5~300.0 58500.0
90.0 93.0 94.0 93.0
54.1 50.1 47.3 44.3
0.00 49.1h 64.60 74.2B
132.9 139.8 132.9 122!7
.0150 .0187 .0170 .0176
.219 .271 .241 .256
EMISSI0N DATA~o***ooo~o*****o*o*****ooo*oo*ooo***o**.oooooooo.o
J
PERCENT BY VOLUME 1.63 2.06 2.50 2.93 3.07 3.80 3.47 3.59
L~. C02 PER LB. OF FUEL 3.14 3.15 3.15 3.15 3.15 3.16 3.16 3.16
) WEI"IiT FLOw, LB./HR. 228.2 2q5.0 34501 405.7 418.9 441.2 419.4 38?3
-
'tI~G) CARBON MONOXIDE
III '0 t-3
~'O I PP~ 8Y IiOLUME 114.1 130..1 122.8 120.2 116. 9 '100 ~ 0- - 106.9
(D(DCD 130.1
:3-..1 LB. PER 1000 LB. OF FUEL 13.969. 12.628 10.465 8.411 7.351 6.175 5.791 5.988
1-0.""
0...--..1. wt:IG"iT FLO~, LB./HR. 1.014 1.144 1.147. 1.082 1.043 .863 !769 .735
)( I
11:1:0 U"4BLlRf~ED rlYDROCAf{BONS AS PPM CARRON
~1- --. ppr~ BY I/OLUME .3.5 1.8 1.4 " .5 .3 h' .'.4 .6 -, .5-- -.-
Lt:i. PER 1000 lA. OF FUE:L .245 .100 .066 .021 .010 .011 .019 .015.
)-- - wEIGHT FLOW. LB./H~. .018 .OO~ .007 .003 .001 .001 !002 .002
. ' --------~ - - - + - - - -
NITRIC OXIDE
J_h- --- -- -. --
. PPM BY VOLUME
LB. PER' 1000' L9. OF FUEL
)-- - ---__m .IJ/EIGHTFLOW'_L~_~HR. -
NITROGEN DIOXIDE
.)---- - ~
PPM BY VOLUME
Ld. PER 1000 LB. OF FUEL
)- - -~- WEIGHT FLOW. LB./HR.
--- - - 16. 0
2.102
-'. _!.153
?1~1
'2.192
.199
-- -5.2
1.054
.077
8.1
1.294
.117
TOTAL OXIDES OF NITROGEN AS N02
(3)
) ---Ch--_-
PPM BY VOLUME -21.3'----- 29.2'
L8. PER 1000 LB. OF FUEL 4.276 4.654
\~E IGHT FLOll,__L_B -'~!:i~-' --- - ----- -.!_31 0 -- --~ _.422
=') --- ---
27.4
2.348
. .257
9.7
1.279
.140
- 37.1
4.879
.535
37.6
2.762
.355
41.4
2.896
.385
- 47.4 - - - - 54.7
2.685 3.393
.375 .!.451
--+--- --~- --~----
- 50.5 ----
3.028
.372
- --- ----.-- -'-.
--+---------_.-
- -- ..- -- - - -----
-- -- -- ----
'.
9.2--'.--8.7
1.032 .930
.133 .124.
46 ;8
.5.267
. .678
.- '-7;3 ----- 6.9--- w. 6.3
.634 .652 .580
.089 - --____.!087, .07~__- _.--------
- -------- ----.,
-- -- -~ ------ -- -
-~- -- - - ---. -
50.0 -- . +- -54". t------6r~'S. ~ 56.8 --- --------_._~---- -- ---
5.369 4.751 5.853 5.222
.7!.3- _u__.6?4 u~-_.!.!J~------ '~~!_---_____~n____--:-
)m
00000 NOTES 00000 '. .
1.4LL E4ISSI0~S CO~CENTRATInNS COR~ECTED TO tONCENTRATI0~ IN WET EXHAUST FROM COMBUSTIO~ WITH DRY AIR.
2.EIlUIVALENCE RATIO CALCULATED FROM C02.CO, AND HC DATA A~D FUEL CO/.!POSITIOP-I.._. - ._------~-------
3.TOTAL NITROGEN O(IDES CALC~LATED USING NOX CONCENTRATION AND '~OLECULAR WEIGHT OF N02 (46.01~..
. --- -- -~~----
-------
EB
AIRESEARCH MANUF'ACTURING COMPANY OF' ARIZONA
" DIVISION Of' TH&: GARREn CORPQRATIDN
GROUP 3
MEDIUM-SIZE
AUXILIARY POWER UNITS
-------
GTCP&5-180
S/f:J
P-S67 -
EPA~AIRESEARCH E~ISSION PROr,~A~ TEST SUMMARY
0000000000000000000000000000000000000000000000
DATE OF TEst 6/14/71 TYPE OF ~UEL AV.K~ROS.
--_.. - "_'h_~__'----' ---------- ---- -_._------
- STOICHIOMETRIC F/A=--: ~06843 -- - RATED SliP= - 160~0-
REL.HUMIDITY= 12.0 PERCENT SPECIFIC HU4IDITY=
- C -- SHP LOADING ONLY
-- POWER- SETTING -NUMBER 1 -- - 6 - 11 - -
PERCENT MAX. CORRECTED POWER 0.0 - 25.0 49.1
( CORRECTED SHAFT HP 0.0 40.1 78.6
----:--MEASUREO SHAFT HP ,--- --- - -0.-0 --~- 39.9 -78.5-
EXHAUST GAS TEMP.. DEG.F 515.0 585.0 655.0
( - SHAFT SPEED, Nl. RPM 41100.0 41600.0 41400.0
--COMPRESSOR INLET TEMP.,f)F;:G.F - 95.0 ---- 100.0 - 102.0
COMPRESSOR OSCHG. PRES.,PSIA 55.6 55.1 54.8
( CORRECTED BLEED FLO~, L8/MIN 0.00 - 0.00 0.00
----CORRECTED FUEL FLOW, L13/HR-- -122.8 ---'--131.0 - 155.0
- -FA RATIO CALC. FROM EMISSION .0069 .007~ .0091
( EQUIVALENCE RATIO .102 .116 - .133
----- --oooooooooooooooooooooooooooooooooooooooooooooooooOSUMMARY OF
- CARBON OIOXIDE - -
(--::-:-------:- PERCENT BY IIOLU~\E - -- - - ----'-T.41---:--- 1 ~62- -- _1.85
LB. C02 PER LB. OF FUEL 3.12 - 3.12 3.12
(---'-~ ~EIG~_T ~LOw, LS./HR.382.6 421._2 483.6 ---- ---
-.;> -;;l CARBOri 110NOX IDE
I&:g '?l - -
(1) CD Q) !
::I ...,j I
I-'~~'
I I-' ~'...,j II
>C I ,
tI:I~:
- ..1 UNBURNED HYDROCIIRRONS AS PPM Co\RHON
(---- - - -- PPHHBY-VOLU'~E ,- -------
LB. PER 1000 LB. OF FUEL
WEIGHT FLOw. LA./HR.
(-,_"":"'"
----------------
ENGINE
C
'L --,- FUEL H/C= 1. 928
DEW PT.= 38.0
PPM 8Y VOLUt~E
LB. PER 1000 L8. Of FUEL
WEIGHT FLOW, LB./HR.
146.13 --
20.582
2.521
-180.8
19.3b1
3.002
1"0.9
19.139
2.104
. --- -- - - -..
(- --
26.3
2.104 '
.258
24.1
1.729
.237
20.8
1.214
.198
- - _.-- ---..
- -. - ~ -
NITRIC OXIDE
(---- ----
- -12.-0
1.804
.222
-14. '+
1.900
.260
~ 28.1
3.229
.501
-- PPM BY IIOLU~E
LB. PEA 1000 LB. OF FUEL
WEIGHT FLOW, L~./HR.
I
~ (- ---------
NITROGE~ DIOXIDE
- -lb -
73.2
117.2
-- 116.9
- 730.0
41300.Q
102.0
54.4
0.00
-- - 177.0
.0105
.153
REDUCED
~- 2 . 1 3
3012
552.6
-200.2
18.721
3.314
--- - ..- _._---
- 18.2
. -- !..915
.113
22.0
2.208
.391
-- RATED EGT=1150.0 DEG.r- RA!ED SPEED= 40700.0
.00501 BAROMETRIC PRESSURE=28.70 IN HGA
COMBINATION SHP/BLEED LOADING
20 - 22 - 19 - 15 10 -5
96.8 96.3 71.9 48.4 24.3 0.0
154.9 154.1 115.0 77.4 38.8 0.0
154.9 154.5 115.6 - --77.9 39;0 0.0
815.0 1150.0' 11~0.0 1150.0 1150;0 1150.0
41100.0 41000.0 41000.0 41100.0 41200.0 41200.0
104.0 - - 107.0 - 110.0 -111.0 - 110;0 - 114.0
53.6 50.0 49.0 47.5 46;0 44.1
0.00 66.12 86.54 100.31 115.~7 132.81
-- 207.0 279.5 212.5262.5.- 251.5 241.5
.0119 - .0168 .0157 .Ol~6 .0162 ,0167
- .174 .245 .229 .228 .236 .244
EMISSION DATAoooooooooooooooooooooooooooooooooooooooooooooooooo
2.42 - - -- - 3.40 -- - -3.17- -3.16 ,- 3.27 3.38
3.12 3.13 3.13 3013 3.13 3.13
645.9 87<;.6 8~c.5 82~.5 786;8 756.0
- - -.. . --- --- -- --. --. .-'- -- ~. - - --" - --
-235.7 - 222.1.:1 252.1 277.9 261.8 248.4
19.382 13.088 15.832 17.483 15.926 14.627
4.012 3.658 4.314 4.589 4.005 3.532
-~- --------- --- --- -.-
'27.3 6.!:r 7.6- 8.5 6.6 - 5.6
1.284 .228 .211 .301 .231 .190
.266 .064 !01~ .081 .058 .046
26.5
2.333
.483
40.3
2.712
- ~139
37.3
2.516
.661
42.1
2.743
.690
44.6
2.817
.680
44.7
2.811
.186
( - -- ~- -- - PPM BY VOLUME. 6.7-- 13.2 .4 - 10.4 11.6 10.5 11.8 13.8 11.9 10.9
L8. pER 1000 LH. OF FUEL 1.542 1.654 .066 1.597 1.562 1.009 1.220 1.422 1.190 1.050
C- WEIGHT FLOW. LB./HR. .189 .221- .-010 .283 .323- .282 .333 - .373 .2~9 .253
- --, - -
TOTAL OXIDES OF NITROGE"J AS N02 (31
( -- - ---- PPM BY VOLUME - ~ . - 18.1 - 22.7 28.5- 32.4 38.0- - 55.1 52.1 51.1 54.0 - 55.5
LB. PER 1000 LB. OF'FUEL 4.307 4.567 5.016 4.982 5.138 5.318 5.319 5.280 5.396 5.368
r WEIGHT FLOw, La./HR. .529 .626 .778 ~882 1.064 1.486 - l! 466 1.386 1.357 1.296
C.... -
00000 NOTES 00000
, (- - _. - I.ALL EMISSIONS CONCENTRATIONS CO~RECTEO TO CO'~CE'\jTRATIC\" IN wET EXHAUST FROM COlo\aUSTION wITH DRY AIR.
~.EQUIVALENCE RATIO CALCULATED FROM C02.CO, AND HC DATA AND FUEL COMPOSITION.
3.TOTAL NITROGEN O~IOES CALCULATED USING NOX CQNCENTRATION AND MOLECULAR WEIGHT OF N02 (46.011.
-------
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J
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)
)
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,
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,
, >a:x- C)
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, 1<0 '"C I
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ENGINE
S/IIJ
P-507
EPA-AIRESEARC~ E~ISSIo~ PROGRA~ TEST SUM~AQY
0000000000000000000000000000000000000000000000
O~TE OF TES~ b/14/?1 TYPE OF ~UEl AVIA.KtRO.
GTCP85-180
fUEL I1/C=I.928
DEW PT.= 39.0
STOICHIOMETRIC f/A= .06841 RATED SHP= 160.0
REl.HUMIDITY= 12.0 PERCENT SPECIFIC HU~IDITY=
, SHP LOADING ONLY
POWER SETTING NUMBER 1 ~ 11
PERCENT MAX. CORRECTED POWER 0.0 ~4.q 49.6
CORRECTED SHAFT t1P 0.0 39.7, 79.3
MEASURED SI-1AFT I-1P 0.0, 39.5 19.0
EXHAUST GAS TEMP., DEG.F 510.0 580.0 645.0
SHAFT SPEED, Nl. RPM 41100.0 41400.0 41400.0
CO~PRESSOR INLET TEMP..DEG.F 105.0 104.0 104.0
COMPRESSOR DSCHG. PRES.,PSIA 54.2 53.? 53.2
CORRECTED 8LEED fLOW, L~/MIN . 0.00 0.00 0.00
CORRECTED FUEL FLOW, lR/HR 116.0 134.0 153.0
FA RATIO CALC. FRO~ E~ISSION .0065 .0077 ,0087
EQUIVALENCE RATIO .095 .112 .127
oooooooooooooooo*oooooooooooooooooooooooooooooo**OSUMMARY OF
CARBON OIOXIDE . '
16
14.9
119.3
119.3
710.0
41100.0
104.0
53.3
0.00
115.0
.0102
.149
~£OUCEI)
RATED EGT=1150.0 OEG.F RATED SPEED= 40700.0
.00524 6ARO~ETRIC PRESSURE=28.58 IN HGA
CCMBINATION SHP/BLEED LOADING
20 22 19 15 10 5
99.1 98.0' 73.8 ' 48.4 24.3 0.0
ISQ.5 156.8 118.0 77.5 38.9 0.0
157.8 156.3 111.8 71.4 38;9, 0.0
190.0 1150.0 11~0.0 1150~0 1150~0 1150.0
41000.0 40600.0 40600.0 40600.0 40700.0 40800.0
104.0 105.0 101.0 108.0 108~0 107.0
53.3 49.7 48.6 46.9 45.6 43.1
0.00 70.08 89.54 101.18' 124.04 131.1.
194.0 211.5 271.5 '260.5, 252-5 235.0
.0116 .0164 .0163 .0162' .0165 .0169
.169 .240 .238 '.231 .241 .241
EMI5SI0~ DATAooooo*ooo*ooo*oooo**o*o~oo*ooo*oo*ooooooooo*oo**.*
PERCENT BY VOLUME 1.33 1.56 1.78 2.07 2.35 3.34 3.30 3.29 3.34 3.43
LB. C02 PER L8. OF FUEL 3.12 3.13 3013 3.13 3013 3.14 3.14 ,3.14 3.14 3.1'+
"IE.IG~T .FlOW. LB./HR. 362.0 .418.9 41~.5 547.1 607.1 85!.9 851.3 81~.1 19~.6 737.0
C'ARSON i>\ONOXIOE
PPM BY VOLUME 125.3 128.1 140.1+ 152.8 177.3 114.3 194.5 194.6 198.7 193.1
lB. PER 1000 ll3. OF fUEL }8.699 16.298 15.116 '14.680 15.001 10.433 11.148 11.812 11.814 110 240
WE-IuHT FLOw. lB./HR. 2.169 2.184 2.405 2.569 2.911 2.833 '3!189 3.017 2.998 2.641
UNBURNEL> HYDROCARBONS 115 PP~ CARRON
PPM'BY VOLU~E 16.9 12.4 11.5 8.7 7.1 1.0 2.1 2.5 .. 2.2 2.0'. ._c,
lB. PER 1000 lB. OF FUEL 1.443 .902 .735 .476 .341, .033 .074 .088 .076 .066 '
WEIGHT FLOir/, LB./HR. .161 .121 .112 .083 .066 .009 !020 .023 .019 .016
. -----. ----.
NIT~IC OXIDE
. PPM BY VOLUME 11.4 ' 14.9 17~7 22.4 27.2 ' 44.4 ., 43.5" 4'1.7' 43.0 43.2
l8. PER 1000 lB. OF FUEL 1.820 2.034 20119 2.301 2.4b6 2.841 2.818 2.711 2.752 2.695
WE.IGHT flO\'I. LB./HR. .211 .213 .324' .403 .478 .113 !,16S ~106 .695 .633
--- - --- "- - .- --- -
NITROGEN DIOXIDE
, 7.3 8.5 10.3 10.9 .10.0 9.4 10.0' 9.1' ,'.9.5
1.524 1.569 1.620 1.510 .919 .934 .998 .889 ,'.910'
.204 .240 .284 .293 ..266 !,254 .260 .2~4 .214
--- -- ----- -. - _.- --..-- ~.~-
22.2 26.2 32.6 '38.1 54.4' .53.0 . 51.7' 52.1 ,.. 52.1
4.642 4.818 5. 14B 5.291 . . ,5~344 5.255 5.154 5.109 5.041
.622 .137 .901 1.021 j:' :.~ct~"~I_,.:. 1!,427 1.343 1.290 '1.185
. . --.- --- --. -.---- . u_- --- -- - ~-- -. ---
PPM'13Y vOLUME
L8. PER 1000 LB. OF FUEL
WEl~HT FLOW. LB./HR.
.' '5.9
1.451
.169
TOTAL OXIDES Of NITROGEiIJ AS N02
PPM BY VOLUME'
lB. PER 1000 lB. OF FUEL'
~EIGHT FLOw, LB./HR.
(31
11.3
4,.247
.493
)._.n h,
- -- - -. - ---
***ojNOTES 000*. " ' ,
1. ALL EMIS~IONS CO~CENTRATIONS COR~ECTEO TO CONCENTRATIO~ IN WET EXHAUST FPOM COMaUSTION;WITH DRY.AIR.
2.EQUIVAlENCE RATIO CALCULATED FRO~~ C02.CO. AND HC DATA AND FUEL COMP05ITIO~.7"~ ----__._._mn___. -
3.TOTAL NITROGEN O~IDES CALCUlATED:~StNG NOX CONCENTRATION AND MOLECULAR WEIGrlT'OF N02 (46.01~.
--------
-------
c
L ---,-
c
c -- --.~-
c_---
(: - - ---
. (--- - - --
".-
('--. -- - -
SIN
- PPM BY VOLUI-IE
LB. PER 1000 l8. OF FUEL
~EIGHT FLO~, LB./HR..
-- PPM BY- VOLUME
LB. PER 1000 LB. OF ~UEL
W~IGHT FLOW. lB./HR.
NITRIC OXIDE
--PPM AY VOL.UME
LB. PER 1000 LB. OF FUEL
WEIGHT FLOW, LB./HR.
- . . .
NITROGEN OIOXIOE
- PPM g Y VOLUI'IE
La. PER 1000 LB. Of fUEL
wEIGHT FL.OW, L.B./HR.
TOTAL. OXIDES Of ~ITROGEN AS ~02
PPIo1-BY VOLUME.
LB. PER 1000 LB. OF FUEL
WEIGHT fLOW, LB./HR.
P-518 .
.. EPA-AIRESEARCH EMISSION PRDGRAM TEST SUMMARY
----.-------O-oooooooooooooooooooooovoooooooooooooooooooooo
. . .- -- ~
~---------- ----- ----------~-~-
- 160.8-
?2.908
2.126
-4.0'...;-
.323
.038
-- - - -
8.4
1.275-
.152
- 8.8
2.070
.246
(31
17 .2
4.025
.419
D~TE OF TEST
6/15/71
TYPE Of fUEL 4VIA.K~RO.
1.61 --. - 1~87----
3.11 3.11
429.8 48~.4
199.0
24.449
3.374
5~ 1
.360
.050
10.2
1.338
.185 -
11.5
2.330
.322
21.7
4.3131
. .61)5
255.3
26.981
-..236
6.3 ..
.383
.060
12.5
1.416
.222
12.7
2.206
. .346 -
25.2
4.311
.687
- 2.10
3.11
5480, 0
. - - - - -.-
-- 266.1
25.051
4.410
5.3
.283
.050
15.4
1.551
.273
15.5
2.402
.423
30.9
4.780
.841
-- -2. 47 -
3.11
621.5
- ---- -- ----
-311.5 -
24.984
5.034
4.3
.199
.040
19.5
1.678
.338
14.4
1.901
.383
34.0
4.474 -
.901
3.70
3014
883.4
3.41 -
3.13
83~.7
181.2 - - - 282.9
10.117 16.496
2.848 4!.429
..6
.018
.005
48.3
. 2.794
.787
9.4
.836
.235
57.7
5.120
1.441
- - -. .
- -7.1
.237
!.064
39.8
2.486
!.667
- 10.2
.918
!.263
50.0
4.789
1.286
3.36
'3.13
81°! . 3
298.2
17.642
4.613
-
9.7
.329
.086
36.8
2.334
~610
12.4
1.210
.316
49.3
4.788
1.252
(
*0000 NOTES 00000
I.ALL EMISSIONS CONCENTRATIONS CQRRECTEO TO CO~CENTRATIa~ IN WET EXH~UST fROM COMBUSTION wITH DRY AIR.
2.EQUIVALENCE RATIO CALCULATEO FRO~\ C02.CO. AND HC DATA AND fUEL. COMPOSITION.
. 3.TOTAL. NITROGEN OXIDES CALCULATED USING NQX CONCENTRATION AND MOLECULAR WEIGHT OF N02 (46.011.
o ENGINE GTCP85-180
CO . \ .
"----- FUEL H/C=I.92S-:--STOICHIOMETR'IC F/A= .06843 - RATED SliP: 160.0 - RATED EGT:Il50.0 DEG.f RATED' SPEED= 40700.0
. DEW PT.= 36.0 REL.HUMIDITY= 13.0 PERCENT SPECIFIC HU~IDITY= " .00462 8AROMF-TRIC PRESSURE=28.63 IN HGA
(------ . - - - -- - - SHP LOADING ONLY COMBINATION SHP/BLEED LOADING
.POWER SETTING-NUMBER . -1- - - 6 - 11. . - - 16 -- -- m 20 - . 22 - 19 15" - 10 5-
PERCENT ~~x. CORRECTED POwER 0.0 25.7 49.9 . 74.5 99.6 98.3 73,0 48.8 24.4 0.0
( CORRECTED SHAFT HP 0 . 0.0 .41.2 79.9- 119.2 159.4 157.3 116.8 78.1 39.0 0.0
----'MEASUREDSHAFTHP-:-------------O.O '----40.8-- 79.3' -118.3 158.3 156.8. 117.2 78~3' .39;1 0.0
-.' . EXHAUST GAS TEMP., DEG.f 490.0 565.0 635.0 710.0 805.0 1150.0 I1S0.0 1150.0 1150;0 1150.0
(~_SHAFT SPEED, Nl. RPM. 41600.0 41500.0 41300.0 .41100.0 41000.0 40600.0 40700.0 40800.0 40800.0 40900.0
. COMPRESSOR INLETTErW..OEG".F. 96.0 - - --96.0 - -' 98.0 .. - 98.0 -99.0- 103.0 '110.0 - 110.0 IlO~O'. 110.0
COMPRESSQR DSCHG. PRES..PSIA 54.8 54.6 53.9 53.5 53.0 49.8 49.0 47.7 46~4 44.1
C CORRECT~D BLEED fLOW. L8/MIN 0.00 0.00 0.00 0.00 0.00 73.35 88.13 104.08 120.55 135.61
...:..---- CORRECTED FUEL FLOW, LR/HR -119.0 138.0 - 157.0 176.0 201.5 281.5 268.5 261.5 253'5 248.5
FA RATIO CALC. FROM EMISSION .0068 .0079 - .0092 .0104 .0122 .0183 .0169 .0166 ~0170 .0173
C. EQUIVALENCE RATIO ..100 .116 .135 .152 .179 . .267 .241 .243 ..248 .252
"--~-ooooo*oooooooooooooooooooooo*ooo.ooooooooooooooooOSUMMARY OF ~EDUCED EMISSION DATAoooooooooooooooooooooooooooooooooooooooooooooooooo
. CARBON LJIOXIDE
. L ------- - --PERCENT BY- \iOLU~IE n "-- - 1039 - n-
. LB. C02 PER LB. OF_FUEL 3.12
( ;.- - "-- - ---_\~ I~~.~.':-'!.W_~ --~~ ~IH~~- - -~______3 ?_O ~ ~- --- ---- --- -
.--'---1 CARBON ~10i~OX IDE
(~06"~ :
( I I
~~ I UNBURNED HYDROCARBONS AS PPMCARRON
I
~~----
(.
3.42
- 3.12
- 792 ~ 0
314.6
18.213
4.632
11.1
.368
.093
37.0
2.303
.584
12.1
1.158
.293
49.1
4.689
1.1~9
. - ..-..
>
--j
3.48
3.13
776.7
309.4
17.667
4.390
.9.8
.320
.080
37.8
2.313
.575
..- -~. . - ~
11.5
1.080
.268
49.3
4.626
-------
)
~)
,
)
, )
)
)
- ),
, 'j
I
'tI)oG)
- I,g;g 7
IDIDOO
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~Q.~
I~~.~
1:Jj::tl
)~~=~.
}----
J- ------
ENGINE
GTCP~5-180
S /1'.1
P-595
DaTE OF TEST
E>/15/!1
EPA-AI~ESEAR~H E~ISSION PQOG~AM TEST SUMMARY
0*000000000000*****0*0000000000000000000000000
TYPE OF FUEL AVIA.K~RO.
RATED SHP= 160.0
SPECIFIC HU4IDITY=
SHP LOADING ONLY
POWER SETTING NUMBER 1 6 11
PERCENT MAX. COR~ECTED POwER 0.0 ~5.4 49.4
CORRE-CTED SHAFT HP 0.0 40.7 79.0 '
MEASURED SHAFT HP 0.0 40.7 19.1
EXHAUST GAS TEMP., DEG.F 510.0 5~0.O 660.0
SHAFT SPEED. Nl, RPM 41600.0 41400.0 41200.0
COMPRESSOR' I~LET TEMP.,DEG.F 105.0 106.0 107.0
CO~PR£SSOR QSCrlG. PRES..PSIA 53.4 52.9 52.6
CORRECTED BLEED FLOW, L~/MIN 0.00 0.00 0.00
CORRECTED FIJEL FLOW, LB/HR 114.0 133.0 153.0
FA RATIO CALC. FROM EMISSION .0068 .0077 .0091
EQUIVALENCE RATIO ' .099 .112 .133
oooooooooooooooo****oooo**oooo**ooo*****oo**ooOOOOSuMMARY OF
CARBON DIOXIDE '
FUEL H/C=I.928
DEW PT.= 36.0-
STOICHIO~ETRIC F/A= .n6R43
REL.HUMInITY= 9.0 PERCENT
16
73.9
11A.2
118.3
140.0
41100.0
101.0
52.4
0.00
}74.0
.0103
.15(\
~EDUCE!)
RATED EGT=1150.0 DEG.F HATEO SPEED= 40700.0
.00462 8A~04ETRIC PRESSURE=28.64 IN HGA
COMBINATION SHP/BLEED LOADING
20 22 19 15 10 5
'9A.7 91.7 72.9 48.8 25.0 0.0
151.8 156.4 116.6 18.0 40.0 0.0
151.9 157.2 111.2 18.3 40;1 0.0
850.0 1150.0 1150.0 1150.0 1150;0 1150.0
40900.0 40100.0 40700.0 40800.0 40800~0 40800.0
- 101.0 112.0 112.0 110.0 110.0 110.0
51.9 49.6 ~9.1 48.5 47.2 45.7
0.00 63.40 86.16 104.91 116.~1 133.42
20.5.0 . 266.5 261.5 264.5 251.5 241.5
.0.120 '.0176 .0163 .0160 .0161 .0164
.175 .251 .239 .234 .235 .240
EMISSION DATAoooooooooooooooooooooo*ooooooooooooooooooooooooooo
PERCEi'JT BY VOLUME 1.38 1.55 1.83 2.08 2.42 3.55 3.30 3.23 3.25 3.32
L8. C02 PER LB. OF FUEL 3.10 3.10. 3.10 3.11 3.11 3.14 3.13 3.13' 3.12 3.12
wEIGHT FLOW, LB./HR. 353.4 412.0. 474.0. 540.1 638.0 83S.a ,818.1 82~.6 78~;1 753.8
CARBON f10NOX I DE
PPM BY VOLUME 190..9 227.3 213.6 261.2 - 288.3 ' 197.3 265.7 289.6' - 324.3 331.5
L8. PER 10.00. L8. OF FUI;:L 27.371 28.955 29.413 24.884 23.555 .11.079 16.0.24 11.819 19.847 19.865
WEIGHT FLOW. LB./HR. 3.120 3.851 4.500. 4.330 4.829 .2.953 4!_190 4.713 4.992 4.797'
UNBURNED HYDROCARBONS AS PPM CARBON
PPM BY VOLU'IE' 50.8 55.5 56.3 49.0. 36.9 6.3 5.7 --- 7.9 13.0- 14.8-
LB. PER lOOo.L8. OF FUEL' 4.162 4.039 3.458 2.670 1.126 .201 .196 .277 .456 .50.7
WEIGHT FLOW, LB./HR. .~74' .531 .529 . .465 .354 .0.54 !051 .073 .115 .123
- - - .- - -. -
NITRIC OXIDE
PPM BY VOLUME -
LB. PER 1000 LR. OF FUEL
)---------- _WEIGHr FLOW. LB./HR.
NITROGErl DIOXIDE
. )~ -
)-
PPM BY VOLUME-
LB. PER 1000 L8. OF FUEL
.WEIGHT FLOW. LB./HR.
- --- ---- --_. -.. -.- -
8.7 11.2 - 13.1 17~3 23.3' 51.6--- 43.1 37.8 35.4 35.6
1.333 1 .535 1.512 1.764 2.041 3.102 2.786 2.493 2.320 2.285
.152 .204 .231 .307 .418 .827 !.729 .659 ' .584 .552
8.1 11.2 -- 12.5 14.-1 . 15.3 8.8 . 11.1 15.0 14.7 14.-6.
2.0.43 2.345 . 2.206 2.200. 2.0.54 .815 1.099 1.516 1.475 1.440
.233 .312 .338 .383 .421 ..217 !.287 .401 .3!1 .348
--. - - - -- -- - n_.- - -. - - - - .--- - ------ --- -. - _.-- .---
oj'
TOTAL OXIDES OF NITROGEN AS N02
)--- -.- -
60..4-- ------ 54.2
5.571 05.370
1.485 1!404
50.1-
5.0.32
1.265
-- --50.2-
4.942
1.194
17.4-
4.0.86
.466
25.6
4.524
.692
--- 31.3-- -- 38.6
4.905 -5.184
.854 1.063
52.8 - --
5.339
1.412
22.4----
4.698
.625
- -~-_. -....------- .,-
------- --
PPM 9Y VOLUII1E---c---- -- --- U.---
LB. PER 10.00 LR. OF FUEL
:: )----____W':I_G_~TJL~w..' -~~~~~~;--
- - -----
--------- .
- --~-----'-_. ---
-.-- -- -------- --
-- - _.- ----- _._---
0000* NOTES 0**00 -
)---- --- -. 1. ALL Ei-.jISSIONS CO:~CENTRATlI'HJS CORPECTED TO CONCENTRATlO'll IN WET EXHAUST FROM ,COMBUSTION WI1'H DRY AIR.
2.EQUIVALENCE RATtO CALCULATED FROt~ C02,CO, AND HC DATA AND FUEL COMPOSITION. --. ------ --------- --- h,____h__--- --
'3.TOTAL NITROGEN OXIDES CALCULATED USING NOX CONCENTRATION AND ~OLECULAR WEIGHT OF N02 1~6.01).
J
-------
( ~-~~~-------_c.-_~-~~-~~-
._-------_._---_.----~-- ------ -- _0-_--
--,-------- ---~~----..
::i:- 'I! -----.
- --......+-".- -
'- ---c --
.' .,
-C--------~_'-:':______d--___~__h~___~--~-- EP4-AIRESEARCH EMIS-SION PROr,R4M TEST SUMM4RY
. ~ .ooo.oo*~ooo~ooo~o.ooo*oooooooo~oo*ooooo*o*ooo
ENGINE GTCP85-180 SIN P-593: DATE OF TESTb/16/~1 TYPE OF ~UEL lIVIA-~~RO.
RATEO EGT=1150.0 DEG.F R~TE~ SPEED= 40700.0
.00425 84ROMETRIC PRESSURE~28.62 IN ~G~
Ca.1BINATION SliP/BLEED LOADING " i
20 22' 19 15 10 5 3
9,9.8 99.1 74.0 49.0 24..6 0.0 0.0
159.6 -- 158.6 118.4 78.4 39.4 0.0 0.0
158.3 157.5 117.1 78.5 39!3 0.0 0.0
-830.0 1150.0 1150.0 1150~0 1150.0 1150.0 950.0
41000.0 !0800.0 '40900.0 40900.0 41000~0 41100.0 41300.0
98.0 100.0 101.0 - 108.0 106.0 _105.0 104.0
54.0 52.5 51.6 49.9 48.9 47.1 49.8
0.00 64.40 86.16 100.06 115.64 132.58 99.73
208.0 276.5 268.5 256.5 248.5 241.5206.5 i
.0121 .0165 .0163 .0162 .0160 .0165 .0127'
.176 .241 .238 .236 .233 .242 .185
EM I SS I'ON DA T A""""""""""""""",,~""""""""""o""o""""o"""""'H'O""""H'"''.......... .
c--
-- FUEL Ii/C=I.928 - 'STOICHIOMETRIC F/A= .06843 RATED SHP= 160.0
,DEW PT.: 34.0 REL.HUMIDITY= 15.0 PERCENT SPECIFIC HU~IOITY~
(--- ' SliP LOADING ONLY
- POWER SETTING NUMBER 1--" ,II
PERCENT MAX. CORRECTED POWER 0.0': 25.1 49.8
l- CORRECTED SHAFT HP " 0.0: 40.2 79.7,
-ME4SUI1EO SHAFT HP ';--0.0;--- 39.7 -79.1
EXHAUST GAS TEMP.. DEG.F \:500.0; 585.0 655.0
(__d SH4F'T SI'EEO. I'll. RPM 4l600.0! - 41400.0 41200.0
COMPRESSOR INLETTEMP;.OEG.F- : 94.~ -'95.0 98.0
COMPRESSOR DSCHG. PRES..PSI4' S5.~ 54.4 54.1
(---- CORRECTEOBLEEO FLO~. La/MIN o.ori, 0.00 - 0.00
CORRECTED FUEL FLOw, L9/HR 118.0139.0 156.0
FA RATIu C~LC,'FRO~ EMISSION: .0067 .0081 .0092
(EQUIVALENCE RATIO : .098 .l18 .134
-----"..""""""""".""."."""."""""""."."""."""""."".o""""SUMM4RY OF
CARBON OIOXIOE .
(- __n
- -d-'- PERCENT BY VOLUr~E
L8. C02 PER LB. ~F FUEL
WEIGHT FLO~. LB./HR.
l
16
74.7 .
119.6
-- U8.6
, 740.0
41200.0
- 98.0
54.2 .
O. DO,
180.0'
.0104
.152
~EDUCED
- -1.36 -'
3.12
367.6
- 1~81
3.12
48~.6
2.12
- 3.12
561.7
2.45
3.12
649.3
- 3.35
3.13
866.8
3.23
3.13
'117.4 '
3.35
3.13
755.5
-1.64
:3.12
433.4
- -- - - --.
3.30
3.13
84~.3
3.27
3.13
802.8
c-~i! CARBON MONOxIDE
IQ '0 I , PPM B\' vOLUME 143~5, 164.8 - 185.7 -20&.7 ' 23&.9 200.6 214.3' 247.7 256.1 265.7 ,
CD CD CDI
'... g,~, Lf;. PER 1000 LB. OF FUEL 20.864 '19.92"> 19.756 19.373 19.222 11.952 12.931 15.082 15.953, 15.1;109
1U1~1"l WEIGHT FLO\4. l.B./HR. 2.462 2.770 3.082 3.487 3.998 3.305 3!472 3.869 3.91:>4 3.818
.bI:D UNBURNED HYDROCARBONS AS PPM CAR"'O!IJ
(. -- PPM. BY VOLUME 25.0 ' 2&.4" 24.5" 22.4 19.0 3.3 4.8 6.4 8.1
4.2
LtJ. pER 1000 VI. OF FUEL 2.079 1.824 1.492 1.203 .883 0142 .115 .168 .226 .274
{ ! wEIGHT FLOw. LB./HR. .245 .254 .233 .216 .184 .039 !031 .043 .056 .066
-- _.-
NITRIC OXIDE
(
PPM 8Y VOLUME,
L~. PER 1000 LB. OF FUEL
WEIGHT FLO~, LB./HR.
(
NITROGEN OIQXIDE
(
PPM BY VOLUME
LB. PER 1000 LR. OF FUEL
WEIGHT FLOW. LB./HR.
(.-
TOTAL 0l(IOE5 OF NI TROGE'! AS fl02
(:
PPM BY VOLUME
LB. PER 1000 L8. OF fUEL
wEIGHT FLOW. LB./HR.
r
C..... - -.
- 10.1
1.578
.186'
14.7
1.'905,
.265
17.7
-2.018
.315
2h3
2.144
.386
25.8
, 2.242
.466
44.9
2.866
.792
44.5
2.876
~772
39.8
2.&00
.667
39.0
2.519
.641
38.9
2.478
.598
- _._~-
-2.56
3d 1
643.1
,
f..
. (
300.0 I-
:>3.216
4.794
25.A
1.139
.235
24.2
2.005
.414
1.4 9.8 11.0 12.2 13.0 1001 9.7 1201 11.8 11.9 14.0
-1.758 1.956 1.924 1.879 1.731 .989 .958 1.206 1. 198 101 64 1.781
.207 .272 .,300 .338 .360 .274 !257 ;309 .2'!8 .281 .368
(3)
'-P.5 24.5 28.7 33.6 38.8 55.0 54.2 51.9 50.9 50.8 38.2
4.178 4.877 5.018 5.166 5.168 5.383 5.368 5.191 5.152 4.963 4.854
...93 .678 .783 .930 1.075 1.488 1~441 1.332 1.280 1.198 1.002 -,
(
0."". NOTES-"""".
1.ALL EMISSIONS CO~CENTRATlnNS CORRECTED TO CONCENTRATIO~ IN WET EXH4UST FROM COMBU5TIO~1 WITH DRY AIR.
2.EQUIVALE~CE RATIO C4LCULATEO F40M C02.CO. lIND HC DATA ~ND FUEL Co~POSITIoN.
3.TOTAL ,NITROGEN O~IOES CALCULATED USING NOX CONCENTRATIJN AND MOLECULAR WEIGHT OF N02 (46.01).
-------
")
~ "
'J
)
,)
)
J
,}
:)
,
I
'tI;x.G1
,'p,,,, 1-3
, 1.0 '" I
I (I) (I) en
, ::S~
""'0.01:0
I en """ ~
~ I
: I ttI::a
t
,)- md,-
,-:L - -- ----
ENGINE
GTCP85-98CK
DATE OF TEST
EPA-AIRESEARC~ E~ISSION PROG~A~ TEST SUMMARY
~~~~ooo~~~oo~*~o~o~oo~~~~~~~~oo*~oooooooooo~oo
-- SIN
P-35f>48
RATED SHP= 1&0.0
SPECIFIC HU~IOITY=
SHP LOADING ONLY
POWER SETTING NUMBER 1 6 11
PERCENT ~~X. CORRECTED POWER 0.0 25.1 49.4
CORRECTED SHAFT ~P 0.0 40.2 79.1
MEASUKED SHAFT HP 0.0 39.7 78.3
EXHAUST GAS TEMP.. DEG.F 560.0 630.0 700.0
SHAFT SPEED. Nl. RP~ 41500.0 41400.0 41300.0
COMPRESSOR INLET TEMP..OEG.F 90.0 93.0 95.0
COMPRES~OR nSCHG. PRES.,PSIA 53.~ 53.4 52.9
CORRECTED BLEED FLOW. L8/~IN 0.00 0.00 0.00
CORRECTED FUEL FLO~ . L~/MR 122.0 141.6 161.8
FA ~ATIO CALC. FROM EMISSION .0072 .OOB~ .009&
EQUIVALENCE RATIO .105, .123 .141
oo*o~~ooo~o~o~o***~~~oo~o~oo~~*~oo*~~o~~o**~~*O*OOSUM~IARY OF
CARSON OIOXIO£
I
TYPE OF ~UEL AY.KEROS.
RATED EGT=1150.0 DEG.F RATED SPEED= 40700.0
.00194 BAROMETRIC PRESSURE=26.65 IN HGA '
, COMBINATION SHP/BLEED LOADING
20 22 19 15 10 5
~7.3 94.5 71.6 41.5 24.2 0.0
155.7 151.1 114.6 16.0 38.7 0.0
155.4 154.3 116.5 17~3 39!1 0.0
930.0 1210.0 11~0.0 1155.0 1160!0 1160.0
41000.0 40700.0 40800.0 40800.0 40800.0 40BOO.0
104.0 130.0 Il5.0 126.0 120!O 114.0
51.9 48.2 47.1 46.5 46.0 45.0
0.00 38.46 55.5f> 81104 101.34 117.92
214,0 258.0 244.0 244.0 242.0 234.0
'.0131 .0118 .0171 .0173 .0173 .0168
.191 .259 .250 .252 .253 .245
E~ISSION DATAoo~oo*ooooooo~o~ooooo~oooooooo*oooooooooooo*oo*oOt
FUEL H/C=I.928
DEw PT.= 17.0
STOIC~IO~ETRIC F/A= .06843
REL.HIJ'HOITY= 6.0 PERCENT
6/7/!'1
16
73.9
119.2
117.3
805.0
,41100.0
98.0
52.4
0.00 "
184.0
.0109
.159
REDUCED
PERCE.'H 8Y IIOLur'1E 1.'45 1.71 1.9& 2.22 2.66 3.59 3.46 - - 3.49 ,3.50 ' 3.40
LB. C02 PER L~. OF FUEL 3011 3012 3.12 ' 3.13 3.13 3.14 3013 3.13 3.13 3.13
I'IEIGHT FLOIO/. L8./HR. 379.0 441.3 505.2 51S.1 669.1 - 60~.O' 11?4.3 764.3 15~.1 732.4
CAR601~ t~ONOXIDE
PPt~ 8Y \lOLv~E 160.7 - 164~9 168.'1 179.8 21?.9 196.2 212.3 216.9 216.0 235.1
U~. PER 1000 L~. OF FUEL' 21.862 19.158 11.138 ,16.133 15.957 10.895 12.228 12.384 12.303 13.789
WEIGHT FLOw. LB./HR. 2.661 2.713 2.773 l.96S 3.415 2.811 2!984' " 3.022 2.977 3.221
, - ..
UNBURr~EO rlYOI~OC ~RBONS AS PPM CARgON
PPM BY VOLU~E 61.1 41.5 29.2 22.0 19.6 15.7 26.3 ' 24.2 24.2 '25.6'
Lti. PER 1000 LB. OF FUEL 4.750 2.757 1.695 1.127 . "38 ' .491 .866 .791 " .789 .858
wt:1GHT FLOw. LR./HR. .580 .390 .274 .207 .179 .128 ~21i .193 .1,!1 .201
- ,-
1.2
.168
.021
9.5'
1.180
.167
12.8
'1.392
.225
',)
, NITRIC OXIDE
I ) -- --- - - '
'PPM'SY -VOLU/oIE---_u --,---,- - -
LB. PER 1000 L~. OF FUEL
wEIGHT FLOW. LB./HR.
-.- . - -.-. -- - - --.-.. - - -----
NITROGEN OIOXIOE
,) --n__u--- --PPM Ry"iiOLUME--- ---- - - 6.5"-------7.7
LB. PER 1000 L9. OF FuEL 1.451 1.464
WEIGHT FLOW. LB./HR. .178 .201
: )'up---,
') --,--- -_u' --
~- )------
)-
"")
7.8
1.291
.210
_.- ----.--
TOTAL OXIDES OF NITROGEN AS N02
(3)
,
'PPM BY vOLUME ------ - un--- -
LB. PER 1000 LB. OF FUEL
WEIGHT FLOW. LB./Hq.
-- ,', 7. T --
1.715
.209
11..2 -
3.273
.463
20.6- -
3.431
.555
- .--- ----- ~ ---- .
._------~-- -. ,---
. - --- ---- .--. - --.--
11.4
1.668
.301
8~0
1.183
, .218
25.4-
3.141
.6C19
22.4,'
1.796
.384
-- 8~ 2 '
I.Q13
.217
30.6
3.767
.80&
_. -.------ ~._- --. ---
--35~3-
2.101
.542 '
- 31.6
1.941
~415
30.2
1.850
.451
30.5 - --
1.864
.451
29.3-
1.841
.431
- - _.. ---
6.7 -----. -- 7.6 - 8.5 -- : 8.1 9.0
.608 .121 .800 .156 .870
0157 '.116 .195 .183 .204
"--- -,_.~ - -- - ----
42.0 -
3.829
.988 '
39.2-- - -, 38.8 - --,
3.106 3.636
, ~904 .881
38.6- ---- - 38.3---
3.614' 3.693
.875 ' .864
------ - ---.--- --- --~-- .-
-----------_.-.--- ----.
*000* NOT~S ***0* '
i.ALL EMISSIONS CQ"JCENTRATIONS CORRECTED TO CONCENTRATIO~ IN wET EXH4U5T FRO~ COMBUSTION WITH DRY AIR.
'2.EQUIVALEI\,CE RATtO CALCUL4TED r.ROMCO~.CO. AND HC DATA AND FUEL CO",POSITION.- -, -- -----_u,_U------___'---,-_d
3.TOTAL ~ITROGEN OXIDES CALCULATED USING NOX CONC~NTRATION AND MOLECUL4R WEIGHT OF N02 (46.01~.
--------
-------
EPA~AIRESEARCH EMISSIO~ PROGRAM TEST SU~MARY
---IHHt.IHt...ttttttttttttttIHtttttIHHtIHt.tttt.IHHHtltltItIHHtlt~1t1t1Ht. -:-- ----
P~27692 ' DATE OF' T~ST 5/3/11 TYPE OF~UEL JP5
RATED EGT=1250.0 DEG;F - RATED ~PEED= 40700.0
.00259 BAROMETRIC PRESSURE=28.72 IN HGA
COMBINATION SHP/BLEED
16 -- -. 20 22 -. - 19 , 15
77.6 90.8 50.9 37.7 - ' 25.2
124.2 145.4 81.5 ~0.4 40.3
- ,120.9 141.7 81.0 60.0 - 4~; 1
865.0 9a5.0 1250.0 1250.0- 1250.0
41000.0 40900.0 40700.0 40700.0 40800.0
.- 74.0'-- - 75.0- -,-96.0 -. 96.0 ---98.0-
51.7 51.6 ;52.1 50.7 49.1
0.00 0.00 35.12 : 55.01' 75.37
197.8 - - 232.0 277.5' 258.0 267.0 206.0 201.0
.0119 .0141 .0186 .0180 .0183 .0186 .0173
.173 .204 ,.270 .262 -.267 .271 .251
~EDUCED EMISSION DATA.~Ott!tltltltoltlt.ott~OItItIt.ItItItIt~tto.ltltlt.It.~ItItItIt..ItOItItIt.ItOIt
(-----~-------_._---~
- ENGINE GTCP85~98~
(r -
, '''----;---- fUEL-H/C=1~877 STOICHIOMETRIC F/A= - ;06817 '- -- RATED SHP=' i60.0-
, " DEW PT.= 23.0 '~EL.HUMIOITY= 10.0 PERCENT ',SPECIFIC HUMIDITY=
C - SHP LOADING ONLY
~-- -POWER 'SETTING-NUMBER - -- . -- T- 6' 11 - -
, PERCENT MAX. COR~ECTEDPOWER 0.0 25.9 51.7
( CORRECTED SriAFT HP 0.0 41.5 82.8
- -----MEASUREO SIolAFT ...P-- - ---- 0.0--' 40'-.------80.6-
EXHAUST GAS TEM.p.. DEG.F ' 615.0 - 680.0 750.0
. ( SHAFT SPEED. Nl, RPM - 41200.0 41100.0 41000.0
- ----CO,",PREsSOR INLETTEr~p;-,DEG,.F--'92,.0' - --74.0 -----74.0 -
COHPRESSOR DSCHG. PRES.,PSIh 51.9 51.4 51.7
(CORRECTED BLEED FLO~, LB/MIN 0.00 0.00 0.00
----- CORRECT£OFUEL FLO. . L8/HR 125.5 152.0 - 172.4
FA RATIO CALC. F~O~ EMISSION .0073' .0085 .0101
( EQUIVALENCE RATIO .107 .124 .147
~_. 0 001t1t0 Olt It It ltoO 00 000 .-it-Olt It 00.1t It It Ito ItItO 0 0 1t0 0 1t01t ttlt ItOIt ItItO SU t~MAR Y OF
. CARSON DIOXIDE .
(- ----.---. ,. - - -- - -- -
, . 'PERCENT BY VOLU~tE --- ---- ---t~-4'9~---'
, LB. C02 PER L8. OF FUEL 3.11
'- .-..' --_~~!!GHT_.f~_O'3I--
IQ'tJ I'
(I) (I) Q) I
::I-..J
(!::;~~:
X It
~~, UNBURNE~ rlYDROC4R80~S ASPPM CARRON
C-.-- __I
SIN
'PPM BY VOLU'IE, ,. - -
LB. PER 1000 LA. OF FUEL
WEIGHT FLOw, LB./HR.
. -- . - --. -
PPM-ey VOLU'-\E
" LB. PER 1000LS. OF FUEL
., C.. .----'- -- WE.IGt'l..'t: FlO;o/. L~./HR.
NITRIC OXIDE
(----.---- ---- - ----,'
PPM BY VOLU'IE
L~. PER 1000 LB. OF FUEL
WEIGHT FLOw. LB./H~.
- . -- - --.
(-- ----
( -----
NITROGE~ DIOXIDE
- P~'" BY VOLU"'E
LB. PER 1000 LB. OF FU~L
WEIGHT FLO~. LB./HR.
(
c--
TOTAL OAIOES OF ~ITROGE~AS ~02
.- --- "PP,", -8Y \/OLU'1E - ---. -- - --
LB. PER 1000 LB. OF FUEL
WEIGHT FLO~. LB./HR.
. --- - -- - ~ .-
(:..
-- - 212.9 -
28.258
. 3.54~__. .
53~'6
~.068
. .511
- - a.1
1.150
.144
1'3,3
2.901
.364
(31
21 .'4 --
4.663-
.585
1 ~'73-
, 3'.12
473.6
- 229.-4' ---
26.258
3.991
- -'49;6--
'3.243
.493
10.1 -
.1 .244
.189
13.8
2.587
. .393
-23.9
4.494
.683
2.06
3.12 .
- - ___5.3! ~. 8- '
262.3
25.307
4.363
- - - - - 0- -- -
43.5
2.401
. .414
14~4
1...88
,.257
14.8'
2.350
.405
, 29.2
, 4.~31
, .-798
-2.41
3.13
61 ~ . 3
275.0
22.693
4.489
33.7
1.592
.315
21.9
1.940
.384
14.0
1.896
.375
35.9
4.871
.963
2.86 --
3.14
727.4 '
, - 260.8 --
18.215
4.226 '
-16.3
.649
.151
- --~. -.
-- ,32.4
2.4-21
.562
12.8
1.472
.342
45.2
5.184
1.203
, j. 78 - --
: 3.15
875.4
130.1 .
6.934
1.924
1.3 "
.038
.011
60.9'
3.459
.960
- 8.6
.753
.209
69.5
6.056
1.681
~ --. ------
--- ------~---- -------
- 3~ 67--
3.15
813.6
142.5
7.797
2!012
2.1 --
.066
..017
.... -- -.._-
58.9
3.454
_!_891
9.0
.805
..208
67.9
6.101
1~574
3.74
3.15
841.9
146.0
7.845
2.095
1.7'
.052
.014
. ~ - ----- ~-
56.5
3.250
.868
9.7' '
.856
.229
66.2
5.839
1.559
, c-
0.0.1t NuTEs OO-ito. -
.. ~- - I.ALL EMISSIONS CONCENTRATIONS CORRECTEn TO CONCENTRATIO~ IN ~ET E~HAUST FROM COMBUSTION WITH DRY AIR.
2.EQUl~ALENCE RATIO CALCULATED FROM C02.CO. ANO HC DATA AND FUEL CO~POSITION.
3.TOTAL NITROGEN OAIOES CALCULATED ItSING NOX CONCENTRATION AND MOLECULAR WEIGHT OF N02 146.011.
r
LOADING
, 10
25.1
40..1
40.0
1235~0
40700.0
, 100;0
45.1
3.79
3.,5
64'!.2
171.4
9.078
1.8!0
.. - -- u_- - -
-.3
.009
.002'
55.2
3.132
.6~S
9.1
.795
.164
64.3
5.598
1.153
5
0.0
0.0 ,;'
0.0/
1200,'0
40800'.0
100.0
43.8
'3.51
3.15
63l.4
214.6--'
12.231
2.459
4.7
0153
.031
48.3
2.950
.593
- ---- - -
11.5
1.076
.216
--j
59.8
5.599
-------
}
')
i )
")
'\
) --
)-
1'tI)O G1
!]I 'U >3
,\0 'U I
IDIDCO
i ::S"'"
\ 1'~~~
>< I
. ~
!XI
)=.~.~
) ....
ENGINE
GTCP85-980
FUEL I1/C=I.877
DEw PT.= 43.0
SIN
1'-27857
EPA-AIRESEARCM EMISSION PROGR~M TEST SUMMARY.
000000000000000000000000000000000000000000000.
D~TE OF TEST 5/6/11 TYPE OF FUEL JP-5
RATED SHP= 160.0
SPECIFIC HU~IOITY=
SHP LOADING ONLY
POWER SETTING NUMBER. 1 6 11
PERCENT MA~. CORRECTED PO~ER 0.0 Z5.1 49.8
CORRECTED SHAFT HP 0.0 40.1 79.6
MEASU~EO SHAFT HP 0.0 39.3 77.9
EXHAUST GAS TEMP., DEG.F 540.0 605.0 . 670~0
SH6FT SPEED, Nl, RPM 41100.0 40950.0 40850.0
COMPRESSOR INLET TEMP.,DEG.F 79.0 78.0 77.0
COMPRESSOR DSCHG. PRES..PSIA 57.9 50.6 56.9
CORRECTED BLEED FLOw, LB/MIN 0.00 0.00 0.00
CORRECTED FUEL FLOw, L8/HR 112.5 137.0 159.5
FA RATIO CALC. FROM EMISSION .0096 .0079 .0094
EQUIV~LENCE RATIO .140? .115 .137
ooooooooooooooooooooooooooooooooooooooooooooooooooSUMMARY OF
CARBO"! DIOXIDE
STOICMIOMETRIC F/A= .06877
REL.HUMIDITY= 40.0 PERCENT
PERCENT BY VOLUME
LB. C02 PER LB. OF FUEL
W~IGHT FLOW, LB./HR.
CARBON MOi~O)( IDE
PPM BY VOLU"1E
La. PER 1000 LB. OF FUEL
WEIGHT FLOW, LB./HR.
1.96?
3.13
351.7
182.2 n
18.537
2.085
UNBURNED HYDROCARBONS AS PP~ CARBON
PPM BY VOLUME
L~. PER 1000 L8. OF FUEL
WEIGHT FLOW, LB./HR.
NITRIC OXIDE
'J. . ---
~ )-----
..)- -----
)
J---
~ " -----
)
-,
PI-'M BY VOLUME
LB. PER 1000 LB. OF FUEL
WEIGHT FLOW, LB./HR'
NITROGEN DIOXIDE
PPM BY VOLUME - .
LB. PER 1000 LB. OF FUEL
WEIGHT FLOW, LB./HR. -- - -
TOTAL OXIDES OF NITROGEN AS N02
-- PPM BY vOCOME
LB. PER 1000 LB. OF FUEL
WEIGHT FLOW,_LBoIHR. -- - ._---
63.6
3.701
.416
... 3.6
.396
.045
1.61
3.10
42!.9
246~9
30.326
4.155
84.8
5.957
.816
7.0
.917
.126
1.90
3.11
495.3
289.7
30.120
4.804
79.4
4.718
.753
10.1
.1.120
.119
---'11 ~~-" -., 13.5.- - --14.5
1.975 2.731 2.484
.222 .374- .396
(3)
16
74.5
119.2
116.7
765.0
40700.0
77.0
56.5
0.00
184.5
.0102
.148
~EDUCED
2.05
3.10
572.2
355.2
34.159
6.302
71.4
3.922
.724
13.3
1.374
.253
RATED EGT=1200.0 DEG.F RATED SPEED~ 40700.0
.00609 BAROMETRIC PRESSURE=28.78 IN HGA .
. COMBINATION SHP/BLEED LOADING.
. 20 22 19 15 10 5
99.6 98.? 73.9 49.2 24.9 0.0
159.4 157.1 118.3 78.8 39.8 0.0
155.8 153.9 115.5 76.9 38;8 0.0
870.0 1230.0 1195.0 1185.0 1175~0 1170.0
40600.0 40100.0 40300.0 40300.0 40400~0 40500.0
76.0 78.0 75.0 .74.0 73.0 81.0
56.453.4 52.7 51.7 SO~5 49.0
0.00 64.'9 79.86 95.59 109.17 119.55
211.0 284.5 273.0 264.0 255-0 234.0
.0127 .0197 .0184 .0181 .0175 .0177
.185 .287 .267 .264 .255 .257
EMISSION DATAooo*ooooooooooooooooooo***oo**ooooo*ooooooooo**ooo
2.57
3.12
658.4.
3.73
3.15
858.7
3.68
3~14
829!3
- - ---
4.00
3.15.
896.6
.334.3
25.786
5.441
212.3 .-
11.543
3~047
138.1
6.917
1.968
201.0
10.796
2!947.
4101
. 1.810
. .382
40.6
1.246
!340
73.3
2.279
.602
41.4
1 . 1 8.4
.337
20.9
1.728
.365
60.3 56.7 - 50.6
3.234 3.265 2.948
.920 - - --_! 8~1._- - ~ !78 - --
9.0--
.744
.212
"--11.9
1.065
.281.
17 . 0 -- - 16 . 5
2.680 2.086
.495, --. . .440
15.5'. -. -lO.5 -- --"24.6 -. ~30.3
2.583 4.137 4.201. 4.786
.291 .567 .670 .883
- - ~ - - --- -
9.6
.84.7
!?31
-. -- 37.4
4.736
.999
-69~3 -.
5.702
1.622
- 66.3 - --- -62.5
5.853 5.585
1!598 1.474
.- -- -- - ____L- --
3.56 .
3.14
80~ol
3.59
3.15
736.3
-- - - - -....
240.5
13-. 5 11
3.445
.202.8
11.302
2.645
76.2--
2.445
.6?4
13-.8-.- -'
.439
.103
47.5.- '--.42.8
2.857 2.554.
.729 .598
11.7-- -12.8
1..077 1.170
---- ._2?~_--_--. .~?..- d'-
59.2-- .
5.458
1.392
55.6-- -
5.085.
1.190
----- -- ----
- ----
-- ----. --
"------ ---..------
00*00 NOTES 00000 .
I.ALL EMISSIONS CONCENTRATIONS CORRECTED TO CONCENTRATIO~ IN WET EXHAUST FROM COMBUSTION WITH DRY AIR.
2.EQUIVALENCE RATIO CALCULATED FROM C02.CO, AND HC DATA AND F.UEL COMPOSITION. - -
3.TOTAL NITROGEN OXIDES CALCULATED USING NOX CONCENT~ATION AND MOLECULAR WEIGHT OF NOt? (46.01).
- ---- -~. --- - -- -..-
-------
..
(:-~---~._---
r
("---FUEl. -i1/C=f .817'-.- STOICHIOMETRIC F/4= -.1)6817 . - RATED SHP= - 160.0-
:bE~ PT.= 17.0 REI..HUMIDITY= 18.0 PERCENT SPECIFIC HUMIDITY=
(--~ -- -. .-' . - ---- -_u- -- ---- _--SHP_.LOADING ONLY
POWER SETTING NUMBER . 1 ' 6 11 16 .
- PERCENT MAX. CORRECTED PO~ER 0.0 24.4 48.5 72.5
(--- ~~=~~~J~DS~~~~\~P_----- ~---~:-~ ----_.~::~---,- -ir:~ ~~t~.-
, EXHAUST GAS TEMP., DEG.F 550.0 600.0' 690.0 800.0
,( __SHAFT SPEED..- Nl, . RPM , _,..41.000 .O_---~O~OO ..0. 40800~ 0- - ~O 700.0
. COMPRESSO~ INLET TEMP..DEG.F 85.0 85.0 88.0.' 90.0-
. COMPRESSOR DSCHG. PPES..PSIA 54.2 5J.9 53.6 53.1
( CORRECTED BLEED FLOw, L8/MIN 0.00 0.00 0.00 0.00
---;---CORRECTED FUELF'LOW , LB/HR -113;0- -. 132~0 -'---154.0' 117!0
~. FA RATIO CALC. FROM EMISSION .0061 .0081 ..0096 .0113
(.__.:.......EQUIVALENCE RATIO. .' - .098 . .111~140' .164
oooooooooooo***ooooooooo*o*ooooooooooooooooo*oooo*SUMMARY .OF REDUCED
. C4RBOl'i, DIOXlOE
( ---- - -- -.'. .. . . -. . - - . -. -- .--
. PERCENT BY VOLU~E
LB. C02 PER L8. OF FUEL
(.-_.-':"_- _\o!.~!i?!iT_F-:LOii,-_L8./HR. .
ENGINE
GTCP85-98
SIN
P-15454
. EPA-~IRESEARCH EMISSION PROGR4M TEST SUMMARY
- 00000000000000000.0000000" 00000 0 0 000000 00000000
DA TE, OF TE.ST . Slll!1 TYPE OF ~UEL. JP5
'RATED EGT=1250.0 DEG.F RATED SPEED~'40700.0
.00194 BAROMETRIC PRESSURE=28.65 IN HGA
. COMBINATION SHP/BLEED LOADING
- - - 20 - 22 - ,- 19 15 10 5
95.8 94.9 11.4 47.6 23.9 0.0
153.3 ' 151.9 114.2 76.2 38.2 0.0
151.6' 150.5 113.2 75.5 37;8 0.0
950.0 1200.0 1200.0 1200.0 1200.0 1200.0;
40500.0 40200.0 40300.0 40300.0 40400;0 40400.0
--.. 94.0' - . 96.-0' 96.0 - . 95.0 '-. '94;0 .92.0
52.5 51.6 50.4 49.4 47~7. 46.4
0.00 49.09 71.53 89.87 106.65 122.05
--208.8 261'.5 251.5 246.5 241.5 231.7
.0138 .0183 .0182 .0179 .0179 .0176
.201 .267 .265 .260 .2~0 .255
E~lSSION OATAoooooooooooooooooooooooooooooooooooooooooooooooooo
-- ----------.----
1-;36--
3.08 .
347.7
1.63 -- --'-1.95
3.10 3.11
4.~_8_.5. 47~.9
2.29
3012
552.8
- 2-.81-
3.1'4
655.1
'3.74
3.15
824.8
'3.71 3.6'4
3.15 3.15
79:?~~.---- ~7t:.6
, 3.63
3.i5
760.4
.3.57
3.15
72~ ~ 0
---.--, -
--~'I CARBON ~10ND,qOE
"I1):oG)"
(.g:g '1 . PPM- BY .VOLU'-!E 279.2--- -- 291.9 - 298.0 282.5 243.5 134.0 144.4 110~4 191.8 214.1
(1)'(1) CD
::1'-' LB. PER 1000 LB. OF FUEL 40.346 35.?36 30.283 24.540 17. ~97 7.200 7.818 9.376 10.~79 12.013
.... a. 01>0 . WEIGHT FLOw, LB./HR. 4.559 4.651 4.664 4.344 3.612 1.883 1~966 2.311 2.555 2.783
(\D~.'-"
X I ' . -.- - - -- - -. --- - -. "- ...- r -
.. ~\ .
.tI:I__! UNBURNED HYOROC.~RBONS AS PPIA C.4RQON
( -. --
-"'-",-:- ---PPM'BY VOLH'iE - -. --- --i12.i' 81./] 51.2 30.1 10.8 . 2.2 3.3 3.6 3'~ 4.3
L8. PER 1000 LB. OF FlfEL 9.260 5.586 2.972 1.494. .440 .067 .101 .li4 .093? .139
,( ~'-:- ---- ~~~ Grl!_fL~>I. - Lq~/Hq. 1.046 .137 .458 .264 .092 .018 ~025 ~028 .023 - .032
..
NITRIC .OXIOE
( ----- . ------ PPI'I -qy-- VOlU'IE -.+ - -- +--- 2.5 4-.9 8.5 22.5' 39.3 37.6 36.4 34.7
13.6 39.2
L8. PER 1000-L8. OF FUEL .388. .629 .923 1.270 1.714 2.258 2'.279 2.218 2.152 2.084
(-,-- . WEIGHT FLOw. LB./HR. .044 .083 .142 .225 .35R .591 !573 .547 .520 .483
--- - n.
NITROGEN OIOXIOE
(--- .- ---PPM BY VOLU'~E 9.4 11.1 9.0 5.1 5.9 5.9 7.1
10.4 10.6 4.9
LB. PER 10011 LB. OF FUEL 2.238 2.059 1.850 1.517 1.054 .429 .455 .531 .536 .652
c-. IoIEI GI-H FLOw. LB./HR. .253 .272 .285 .269 .220 .112 !1l4 .131 .129 .151
. -
TOTAL OXIDES OF i" I TROGPI AS N02 (3)
c--- - --- - - PPIoIBY VOLUME 11.9 is.? 19.6 -:31.6 44.4 -- 43.5 42.3
24.3 44.1 -- 41.7
U,. PER 1000 L8. OF FUEL 2.834 3.024 '3.266 3.464 3.682 3.891 3.948 3.932 3.835 3.847
r WEIGHT FLOw. L~./HR. .320 .399 .503 .613 .769 1.018 !993 .969 .9?6 .891
C..... -
00000 NOTES 00000
c-. 1.ALL E~1JSSIO""S CO~CENTqATI~NS CORqECTE~ TO CONCENTRATION IN WET EXHAUST FRO"! C01~BUSTION \IIITH DRY AIR.
2.EQUIVALENCE RATIO CALCULHED FRO"! CO;!.CO. ANU HC DATIl A'IIO FUEL COMPOS IT I'lN. .'
'3. TOTAL NITROGEN OXIDES CALCULATEO USING NOX CONCENTR4 T I 0." AND t-40LECUL4R \IIEIG,",T OF N02 (46.011.
-------
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ENGINE
GTCP~5-98
5/'1
P-l'='257
EPA-AIRESEARC~ E~ISSION PROGRAM TEST SUMMARY
**********************************************
n,TE OF TEST 5/18/?1 TYPE OF FUEL aV.KEROS.
FUEL I;/C=I.928
DEW PT.= 10.0
RATED SHP= 160.0
SPECIFIC HU~IDITY=
SHP LOADING ONLY
POWER SETTING NUMBER 1 6 11
PERCE~T MAX. CORRECTED POWER 0.0 24.2 48.3
CORRECT~O SHAFT HP 0.0 38.~ 77.3
MEASU~ED SHAFT HP 0.0 38.3 76.4
EXHAUST GAS TEMP.. DEG.F 530.0 610.0 695.0
SHAfT SPEED. Nl, RPM 41000.0 409~0.O 40800.0
COMoRESSOR INLET TEMP..~EG.F 84.0 8~.0 85.0
COMPRESSOR OSCHG. PRES..PSIA 54.9 55.2 54.9
CORRECTED BLEED FLOW, La/MIN 0.00 1.00 0.00
CORRECTED FUEL FLO~ , LB/HR 116.8 136.5- 158.8
FA RATIO CALC. F~OM EMISSION .0073 .0085 .0100
EQUIVALENCE RATIO .107 .124 .146
**************************************************SUMMARY OF
CARBON DIOXIDE
STOIC~IO~ETRtC F/A= .06843
REL.H~MIDITY= 8.0 PERCE~T
16
72.3
115.7
114.3
785.0
40700.0
85.0
54.6
0.00
182.0
.0117
.171
~EOUCED
RATED EGT=1200.0 DEG.F RATED SPEED= 40700.0
.00135 BAROMETRIC PRESSURE;28.84 IN HGA
COMBINATION SHP!BLEED LOADING
20 22 19 15 10 5
95.8 95.7 71.7 47.7 23.9 0.0
153.2 153.1 114.8 76.4 38.3 0.0
15~.0 151.3 113.5 75.6 37!9 0.0
910.0 1200.0 1200.0 1200.0 1200~0 1200.0
40600.0 40400.0 40400.0 40400.0 40500~0 40560.0
90.0 85.0. 86.0 88.0 88.0 88.0
54.0 53.5 52.0 53.2 50.6 48.2
0.00 45.04 70.85 45.99 83.42 116.49
219.5 270.0 270.0 274.0 . 262!0 242.0
.0137 .0184 .0190 .018& .0191 .0189
.200 .270. .277 .273 - .279 .276
EMISSI0~ D.TA~~~******~**~***.*******~*******~**.***~***~*~****
PERCE'-IT BY VOLU~E 1.47 1.71 2..02 2~37 2.78 3.74 3.85 3.78 3.87 3.83
LB. C02 PER LB. OF FUEL 3.06 3.09 3.11 3.12 3.13 3.14 3014 3.14 3.14 3.14
wEIGHT FLOw, I-R./HR. 357.5 421.7 493.5 567.6 686.8 848.8 8~8.9 861.6 1323.9 76~.5
CARBON MONOxIDE
PPM BY VOLUME 288.6 269.1 263.5 253.8 21901 120~8 122.7 - - 115,5 - 117.0 137'tl --
LB. PER 1000 LI3. OF FUEL 38.2A5 31.026 25.788 21.258 15.710 6.46-0 - 6.377 6.111 6.056 1.195 ?
~JEIGrtT .FLO
-------
")
S/tJ
'P-15541
DATE OF TEST
5121/"!'1
EPA-AIRESEARCH EMISSION PROGRA~ TEST SU~MARY
~~******ooo*o***oo**o**oooooo*ooo*ooooo*ooooooo
.--~_._- - -.
{
ENGINE' ,GTCP85-98
- -
.~;.. --'-FUEL-H/C=I;928 - - STOICHIOHETRIC -F/A= ;06843 ---- RATED' SHP=- 160.0
DEW PT.= 28.0 REL.HU~IOITY= 13.0 PERCENT SPECIFIC HU~IDITY=
(--- -, - - - -- _SHP _LOADING ONLY-
" POWER SETTING NUMBER, 1 6 11
PERCENT ~AX. CORRECTED POWER 0.0 24.~ 48.1 -
( CORREC TED SHAFT, HP 0.0 38.7 77.0
,----MEASUREO SHAFT'HP--- -~O.O -h- - 38~1--' -76.0
EXHAUST GAS TEMP., DEG.F 550.0 635.0. '140.0
(__SHAFT SPEED, Nl, RPM 41000.0 40700.0 40600.0
CO"iPR£SSQR INl.ET TEMP.''-DEG.F ,-- - 88.0 n-c-_u 92.0~ - -- 95.0
COMPRESSOR. DS"CHG. PRES.,PSIA.- 51.9 51.4, 51.3
; l-- - - CORREC.TEO BLEED FLOW, L8/MIN 0.00 0.00 0.00'
, r CORRECTED FUEL FLOw- .- LB/HR - -117.0 -125.0--- 158.0 '
- FA RATIO CALC. FROM EMISSION .0070 .0084- .0099
(. EQUIVALENCE RATIO - .102 i123 .145
*ooooooooooooooo*oooooovoo*o*o*********oo***o***ooSur~MARY OF
CARBON DIOXIDE '-
{-~------- ,--- '- -- -, '-
. , PERCENT BY VOLUME
LB. C02 PER LB. OF FUEL
Q ---;-------~~~~~.F:LO~,-~~.~...~~- - ,-, - -- - --u_--
-'1:1 ; -~l CARBON MONOX IDE
1II-'tJ 1-3,
1Q'tJ I -
CDm~
NO.""
t-' .... -..J
>< I
txI::t1
16
71.7
114.8
- 113.5'
865.0
40400.0
- -- 96.0 ---
51.2
0.00
182.0
.0120
.175
REDUCED
----1. 3A -
3.04
356.0
1.68
3.06
3A3.1
1 ~-99-- - - 2.42
3.08 3.11
4~1.' ~- _5_6~ ,_4. ~
----..-.. ---
PPM--B 'fVOLO'~E-
LB. PER 1000 LB. OF FUEL
wEIGHT FLO~. LB./HR.
~282.1- --.319.9
39.535 37.133
4.626 4.642
328.0
.32.414
5.121
296-.4 .
24.188
4.402
-- - - - ._--
UN8URNED HYDROCARBONS AS PPM CAnRON
---------- -'--.-------.-----
TYPE OF ~UEL AV.K~ROS.
RATED EGT=1250.0 DEG.F - RATED SPEED: 40700.0
.00328 8AROMETRIC PRESSURE~28.58 IN HGA
- COMBINATION SHP/BLEED LOADING
20 - 22. 19 . 15 10 5 -
95.5 94.7 70.7 - 47.1 lj.6 OiO
152.8 151.5 113.1 75.4 37.8 0.0
150.9 149.8-- Il2.i -74.7 37;4 0.0-
995.0 1250.0 1250.0 1250.0 1250;0 1250.0
403uO.O 40000.0 39900.0 39900.0 40000~0 40000.0
95.0 - -96.0 98.0 -- - 98.0- 91.0 96.0
51.0 49.0 48.0 46.9 45~7 44.0
~.oo 40.24 65.93 83.77101.01 116.07
213.4 258.3 - 253.4 - 248~4 - 243-4 233.4
.0145 .0195 .0195 .0195 .0192 .0191
.212 .286 .285 .285 ,281.279
EM I SS ION DA T AOOII-O*OO~HtooOOO*oooo~HtOO*~HlOOO*ooo_lfoooooo*ooo******
2~93
3.13
667.4
3.96 ,-- .3.95 3~94
3.14 3.14 3.14
_811.9 -- 795.8 - - --_?~_~.2
3.89
3.14
763.9
3.86
3.14
732.7
-- -
196.1
130304
2.839
-90.1
4.552
1.176
109.2
5.535
10375
114.5
5.875
1.430
100.9
5.100
1!.292
127.6-
6.609
1.542
(,---'-'-'--- -----PP~BY' VOl.UME 222.1 169.8 121.9 13.6 54.1 45;2 68.3 57.6 - 80.1 56.6
LB. PER 1000 LEi. OF FUEL 17.788 11.266 6.883 3.43~ 2.100 1.307 1.975 1.670 2.349 1.674
(-:--- WEIGHT FLOW, LB./HR. 2 . 08.1 1.408 1.088 .625 .448 .338 !.500 .415 .572 .391
- - - _.- -
NITRIC OX IDE
L-- -- - PPM ~Y vOLU"1E -- 5.2 -9.2 14~7 23.9 40.4 61.1 61.3 59.8 59.6 56.3
LB. PER 1000 LB. OF FUEL .785 1.144 1.560 2.092 2.935 3.310 3.323 3.247 -3 . 275 3.124
'- WEIGHT FLO'.o/. LB./H~. .092 .143 .246 .381 .626 .855 .842 .807 .7?7 .729
~.- -
NI TROGEI'>i DIOXIDE
C PPM 8'1' -VOLUME 13.1 -- 15.0 -15.3 13.8 - 7.7 4.9 5.1 4.6 4.1 4.6
-LB. PER 1000 LB. OF FUEL 3.009 2.866 2.481 1.846 .-957 .405 .422 .385 .347 .389
(: --- WEIGrlT FLOw. LB./HR. .352 .358 .392 .336 .183 .105 !.107 .096 .085 .091
-i
TOUl. - 0)1, IDES OF NITROGEN AS -'J02 (3) ~
(------ ------,PPMBY vOLUME 18.-3 2'+.2' 30.0 37.7. 48.1 66.0 66.4 , 64.4 63.7 60.9
LB. PER 1000 LB. OF FUEL 4.212 4.620 4.872 5.053 5.357 5.479. 5.517 5.364 5.369 5.118
C~ wEIGHT FLOW, LB./HR. .493 .577 .770 .920 1.143 1.415 1!.398 1.332 1.307 1.209
*000* NOTES ***00
<- --- I.ALL E~lISSIONS CI)~ICPJT R A TI MIS CORRECTED TO C(lNCENTRA TI 0'1 IN WET EXHAUST FROM COMBUST lOll! WITH DRY AIR.
2.EQUIVI\LENCE RATIO CALCULATED FRO'4 Co~.CO. IIND HC DATA AND FUEL CO~?OS IT I 01\1.
3. TOUl. NITROGEN OXIDF::S CALCULATED IJSING NOX CONCENTRA TI:>N AND M0l.ECULAR \IIEIGI-IT OF N02 146. 0 11.
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S/"'
P-18125
EPA-AIQESEARC~ E~ISSION PROGRAM TEST SUMMARY
~~~*******o*ooo**ooo**oo*o~******************o
o,TE OF TEST 5/13/11 TYPE OF FUEL JPS
GTCP85-11S
fUEL H/C=I.a71
DEW PT.= 42.0
STOIC~IOMETRIC-F/A= .06811
REL.~UMIDITY= ~5.0 PERCENT
RATED S~P= 16n.~
SPECIFIC ~U~IDITY=
SHP LOADING ONLY
POWER SETTING NUMBER 1 (, 11
PERCENT MAX. CORRECTED PONER 0.0 24.2 41.8
CO~RECTED SHAFT HP 0.0 38.1 16.6
MEASURED SHAfT HP 0.0 38.2 16.0
EXHAU5T GAS TEMP.. DEG.F ~20.0 615.0 140.0
SHAFT SPEED. Nl. RP~ 41100.0 40800.0 40600.0
CO~PRESSOR INLET TEMP..DEG.F 82.0 85.0 93.0
CO~PRESSOR OSCHG. PRES.,PSIA 64.1 6~.9 61.0
CORRECTED RLEED FLO~. Ld/MtN 0.00 '0.00 0.00
CORRECTED FUEL FLO~ . L8/HR 110.6 121.1 155.9
FA RATIO CALC. FRO~ EMISSIO~ .0064 .0011 .0097
EQUIVALENCE RATIO .093 .112 .141
o**o***o*********oo*********************~**o*oo*ooSU~~ARY OF
CARBON DIJXtDE . - .
16
70.8
113.3
113.1
'100.0
40500.0
105.0
5801
0.00
185.3
.0124
0180
qEDuCED
RATED EGT=1250.0 DEG.F RATED SPEED: 40700.0
.00586 8AROMETRIC PRESSURE=28.78 IN HGA
. COMBINATION SHP/BLEED LOADING
20 22 19 15 10
95.0 94.270.7 46.1 23.~
151.~ 150.8 113.1 14.8 37.5
]51.3 150.9 113.2 15.6 37;8
101~.0 1200.0 ]200.0 1195.0 1200;0
40400.0 40300.0 40300.0 40400.0 40400.0
96.0 102.0 102.0' 114.0 109!.0
61.9 56.9 54.2 52.6 50.6
0.00 33.08 49.8665.58 85.n3 0.00
215.8 254.5 246.4 234.2 -233-2 -0.0
.0140 .0176 .0174 .0169 .0174 .0172
.204 ,.256 .253 .245 .254 .250
EMISSION D4TA*************************0*00***0*************0**0
5,
0.0
0.0
0.0
-0.0
-0.0
-0.0
PERCENT BY 'IOLU'-1E 1.30 1.56 1.98 2.52. 2.86 3.58 3-;54 3.43 -- 3.54 3.48
Lb. C02 PER LB. OF F'UEL 3.11 3.11 3013 3.14 . 3.14 3.15 3015 3.14 . 3.14 3.14
WEI<;'iT FLOW. LR./tiR. 343.4 318.1 43~ . 1 581.2 611.8 80?0 775.6 73~.4 133.1 u.O
..
CARSON ~tONOX I DE
PPM BY VOLUI'IE --- 196.1 215'-9 211..4 221.1 211.2 161.8 200.4, 226.1 243.1 . 264.3-
LEI. PER 1000 LB. OF FUEL 29.790 21.411 21.224 17.501 15.201:1 9.056 11.347 13.241 13.733 15.166
WEIGI"IT FLOw, LB./H~. 3.295 3.336 3.309 3.243 3.282 2.305 2!196 3.101 3.202 0.000.
UNBURNEu HVDROC~RaO"'S AS PP~ CAR80N
58'-2 54.1 21.0 13.3 6.9 3.0 3.3 4.4- - ~ -- 5.0 8.0- u--:-
5.050 3.961 1.541 .602 .215 .091 .108 .148 .161 .263
.559 .483 .241 . .111 .059 .025 !021 .035 .038 0.000
5.4 8.7 19.5 . 32.0 39.8 48.5 49.9 46.6 - -.. 48.4 .. 45.1
.811 1.181 20102 2.710 2.'185 2.901 3.029 2.916 2.928 2.172
.096 .144 .328 . .502 - .644 .740' ~146 ~6B3 - .683 0.000
-- - --- - - - ---~_.- - --- -..-
10.8 U'-9 9.5 8.1"- ---4.7 . 5. ~ 5.6' ----. '5.8- -6~7 7.5
2.684 2.474 1.574 10136 .546 .520 .517' .551 .623 .709
.297 .301 .245 .210 .118 .132 !121 .130 .145 0.,000
PPi-I BY VOLUME'
LB. PER 1000 LB. OF FUEL
WEIGHT FLOW, LB./HR.
NiTRIC OXIDE
- PPM "BY VOLUr-'E ------ U .
L~. PER 1000 L9. OF FUEL
WEIGHT FLOW, LB./HR.
- - -. - ., -
NITROGEN DIOXIDE
:)-- --_._. 'PPM BY V OLlJ 'IE" --.
LB. PER 1000 LB. OF fUEL
wEIGHT FLOW, L8.-/HR.
0.- -._--
"
,
TOTAL OXIDES OF NITROGE~ AS N02 (3)
)----
40.7
5.291
.980
***** NOTES ****.
I.ALL E~ISSIONSCO'4CE~TRATtnNS CORRECTED TO CO~CE~TRATIO~ IN WET EXHAUST FROM COMaUSTION WITH DRY AIR.
. 2.Ea0IvALENCERATIO CALCULATED FROM C02.CO. AND HC DATA AND FUEL COMPOSITION. . .--- _.-
3.TOTAL NITROGEN OXIDES CALCULATED USING NOX CONCENTRATION AND MOLECULAR WEIGHT OF N02 (46.01).,
). ------- ---------- - --- _n--_- '----'-' ---- '
.: J-
)---
PPr-1 8'( -VOLU~E----- - -~-- -- _Uh
LB. PER 1000 Lq. OF FUEL
wEIG~T FL~W, La./HR.
. - ... - - - - - '----.-- -~_.- ~._~ ---
-- 20-.5--: --- .-. 29.1 -h
4.284 '4.196
.521 .148,
-- 16.1-
4.019
.444
- ----- _. --~- -" --
-- 44.5
5.122
1.105
54.'1"-- - 55.5 --. - 52.4 m- - 55.1' . ._- 52.6----
4.971. 5.-161 5".028, 5.112 4.959
1.2~1___.~ 1.!.2~~ __n _~_'.!78_~__~.1_~2- ___.0.... O~~- -
-----
-------
, '
~, (-p----;--- ---.--. --
EPA~AIRESEARCH E~ISSION PROGRAM TEST SUMMARY
4tItItItItOItItClItClOOOOIHtOItClClOClO.oOClOOOItClOClClItOOClooIHtooCl .,..- - --.--
. O..;.TE OF T~S'T .6/8/71 TYPE OF FUEL AV.K~ROS.',
EGT=1250.0 DEG.F RATED SPEED= 40100.0
BAROMETRIC PRESSURE=28.72 IN HGA
COMBINATION SHP!BLEED LOADING
20 22 19' '15 . . 10 5
96.3 95.5 11.0 41.4 23.8 0.0
154.1 152.8' 113.6 15~9 38.0 0.0
153.i' '152.4 114.3 76~2 -- 38;2 0.0
960.0 1250.0 1250.0 1250;0 [250;0 1250.0
40900.0 40100.0 40100.0 40700.0 40800;0' 40800.0
. . 96.0 - 100.0 110.0 - 108;0 '. -108;0 . 108.0
53.9 51.9 50.2 48;7 41~0 45.3
0.00 44.80 58.98 19.58 96.~3 111.11
216.5 281.5 266.5 256.5 251~5 241.5
.0136 .0183 .0IeO.0179 .0178 .0111
.199 - .268 .263 .262 .261 .259
EMISSION DATAooooooooClooooOOOOItClClItOOOOItClOOOClCloClClClClOClClClOltltltClOClOO
- - - . -------------
---+---
ENGINE
.r
~.... -------FUEL H/C=I.926 ---STOICHIOMETRIC f/A= .06843' . RATED SHP;' -'160.0 HRATED
DEW PT.= 36.0 REL.HUMIDITY= 15.0 PERCENT SPECIFIC HUMIDITY= .0~461
f - '-;- POWER SETTING NUMBER'- - - I?P LOADI~~ ONLY.. - 1'6":- --
PERCENT MAX. CORRECTED 'POWER 0.0 24.4 48.1 72.6
( CORRECTED SHAFT HP 0.0 39.0 78.0 116.1
--- MEASURED SHAfT' HP'--O.038.6- -17.1:p '115.1
EXHAUST GAS TEMP., DEG.F. 545.0 620.0 110.0 .820.0
( . SHAFT SPEED,Nl, RPM " 41200.0 41200.0 41200.0 . 41000.0
- --'-COMPRESSOR INLEl TE>-IP.,DEG.F- 92.0 '91.0" 91.0 '94.0 '
COMPRESSOR DSCHG. PRES..PSIA 53.5 54.4 54.4 54.1
l CORRECTED BLEED FLOW. LH/~IN . 0.00 0.00 0.00 '0.00.
-- -CORRECTED FUEl..FLO.-/ , l.B/HR - . 1'21.6 .. 139.0 -. 161.0 186.2 '.
,FA RATIO CALC. FR01" EMISSION' .0066 .0083 .0100 .0118
(. ' EQUIVAl.ENCE RATIO . .09~ .122 .147 .172
-- -- -ClOOO 0*41 ***OOClOO.I CAR80N
(--~.~--- . - --- BY VOCiJ<.1E- ,------ 6Z. 0 -64.5 .53.8 38.5' 22.1 5.3 12.8 14.3 19.0 23.2
. -~ PPM .
LB. PER 1000 L8.0F FUEL 5.226 4.3?A 2.994 1.831'> .932 .163 .402 .449 .599 .738
( --- .-- - - ~~I~H.r--~,LOw, LB./HR. .' .635 .601 .482 .342 .202 .046 ~101 .115 .151 .178
-- - _. - ---
NITRIC 0)(10£.
C. ---- - ---. - PPM SYVOLU1IE' -- '3.7 5~A ' -- 10.6 14.7 22.8 31.5 31.0 . 35.3 34.9 32.0
LB. PER 1000 L8. OF FUEL .531 .128 10104 1.309 1.759 2.159 2.17'+ 2.011'1 2.064 -."- 1.909
C-.-- WEIGHT FLOw. LR./HR. .011 .101 .178' . _.244 .381 .608 ~519 .533 .5;9 .461
..
NITROGEN D.IO-J .293 .275 .242 0121 !12~ .154 .153 .178
. .. --
TOTAL OI'.IOES OF ."1 TROGE"I AS tl02 (3)
{-- PPM BY VOLUro!E . 11.1 14.7 '22.0 25';4. 32.3 42.4 42.3 41.9 41.6 40.1
LB. PER 1000 LB. OF FUEL 2.698 2.834 3.513 3.483 3.815 3.742 3.805 3.766 3.713 3.663
f WE.IGHT FLOW. LA./HR. .32B .394 .566 .64A .826 1.053 1~014 .971 .949 .885
. C_--u, . --
ClOOClIt NOTES ClOOOO
(.~ 1.ALl. Er"ISSrOIlJS CO'lcE~TRA T r OriS CORRECTEO Tn cO"lCEIIi TRA T[ 0'11 IN loin EXH4UST FROM COMBUSTIJN WITH DRY AIR.
2.Er~UIVALEr~CE RATIO CALCUL oHEO FRO-.4 C02.CO, AND HC DATA A'JO fUEL CO~I?OS I TI ON.
3.TOTAL NIT~OGEN OJiIor::s C4LCULATED USPJG NOX CONCENTRATION "'ND I>10U::CUL4R WEIGHT OF N02 (4~.01>.
-------
")
'J'
')
~ )
:j
',")
'J
:)
I
~ 'tI )0 G)
,:~:g '(
(1)(1)(1)
:3......
,1\)0.01>0
'J 01>0 ..........
'I >< I
) tI:J :0
~.I - - --
.},.:.:~
,. ,
, J--
I
)- -- --,
I
~,
:)--,
; )---
:)
ENGINE
GTCPB5-115
o-I~702
DATE OF TE-ST
EPA-AI~ESEARCrl E~ISSION PROGRAM TEST SUMMARY
0000000000000000000000000000000000000000000000
TYPE OF FUEL
JP4
RATED SHP= 100.0
SPECIFIC ~UMIDITY=
SHP LOADING ONLY
POWER SETTING NUMBER 1 (, 11
PERCE~T MAX. CORRECTED POwER 0.0 25.0 49.7
CORRECTED SHAFT HP 0.0 40.0 79.6
MEASUrlED SHAFT HP 0.0 38.6 76.9
EXHAUST GAS TEMP.. DEG.F 540.0 620.0 705.0
SHAFT S~EEJ). Nl, RPM 41200.0 41200.0 41100.0
COMPRESSO~ INLET TEMP..OEG.F 87.0 90.0 94.0
COMPRESSOR ~SCHG. PRES..oSIA 53.5 53.3 53.0
CORRECTED BLEED FLON. L~/MIN 0.00 0.00 0.00
CORRECTED FUEL FLOW . L~/HR 116.4 138.0 158.0
FA RATIO CALC. FROM EMISSION .0DbR .0079 .0096
EQUIVI-\LEI~CE RATIO .100 .117 .141
- ooooo**o**oooo**ooooooo*~o**o*ooooo*oooooooooo*oo*SU~'~~RY OF
CARBON DIOXIDE'
5/"1
FUEL H/C=I.990
DEw PT.= 35.0
STOIC~IOMETRIC F/A=.06B06
REL.HUMIDITY= 17.0 PERCE~T
6/11/?1
16
74.2
118.1
115.1
830.0
41000.0
98.0
52.6
0.00
183.2
.0111
.112
REDUCED
RATED EGT=1250.0 DEG.F RATED SPEED= 40800.0
.00454 ~AROMETRIC PRf.SSURE=28.00 IN HGA
COMBINATION SHP/BLEED LOADINS'" .
20 22 19 15 10'" 5
98.4 97.1 72.7 48.5 24.3 0.0
157.5 155.4 116.3 77~0 38.8 0.0
153.5 152.4 114.3 76.4 38;1 0.0
955.0 1250.0 1250.0 1250.0 1250;0 1248.0
41000.0 40700.0 40700.0 ~0800.0 40700~0 40800.0
103.0 110.0 112.0 114~0 110.0 114.0
52.3 50.1 ~8.6 46.9 45~1, 43.1
0.00 41.91 60.01 83.80 99.35 111.04
212.0 266.5 262.5 246.5 241.5 .232.5
.0133 '.0188.0187 .0186 .01ij2 .0188
.196 .210 .274 .274 .268 .216
EMISSION OATAOO*ooooooooooooooooooooooo**oooooooooo:ooooooooooo
PERCENT BY VOLur-lE 1.37 1.00 1.93 2.35 2.09 3.18 3.70' :-- 3.H 3.60 3.77
Lb. C02 PER LB. Of FUEL 3.08 3.08 3.09 3.10 3.11 3.12 3.12 3.12 3.12 3.12
i'lEIGfiT FLOW, LBo/HR. 35~.9 425.6 48!.9 567.2 658.9 83i!.4 8i?5 761:1.7 753.0 725.1
CARBON MONOXIOE
PP~ BY VOLU~t: .- 195.0 235.4 279.1 301.6 259.3 192.2 206.6 , 245.5, 243.4 245.6
LB. PER 1000 LB. OF FUI:L 21.85(;> 28.915 28.408 25.264 19.099 10.102 10.922 13.013 13.188 12.924
WEIGHT ;FLOW. LB./HR. 3.242 3.990 4.488 ,4.628 4.049 2.692 2~867 3.208 3.11:15 3.005
UN9UPNEO r1YDROCM~80"'S AS PPM CARBO'"
PPM BY VOLU'1E 55.8 54.9 48.1 31.2 18.3 9.9 11.8 -- 13.4 ' . 13;9' .. 12.5 --~.
LB. PER 1000 LB. OF FUEL 4.553 3.855 ' 2.196 1.493 ".110 .296 .351 .407 .430 .376
WEIGHTJLq"'! L8./HR. .530 .532 .442 .214 .163 .079 !094 ,,100 .104 .087
NITRIC OXIDE
PPM BY .V9LU~E- -_u_--~--
LB. PER 1UQO L~. OF FUEL
wEIGHT fLOW. LB./HR.
~ITROGEN PIOXIdE
7.7
1.171
.131
10.a
1.421
.196
18.2
1.981
.314
~-- -- ---.
pp~ - fly VOLUME -- ----.- - .
Ld. ~ER 10DO LB. OF FUEL
wEIGHT FLO~. Le./HR.
7.8
1.835
,'.214
- 9.8'
1.986
.27~
8.0
1.341
.212
__n__._-
TOTAL OXIDES OF NITROGE~ AS N02
(3)
27.0
2.420
.443
35.3
2.780
'.591
58.3 -
3.280
,.814
56.8 --
3.216
~844
58.'1 '
3.300
.813
--54.4---
3.159'
.76.3 .
54.1 -
3.052
, .709
.. - - - -
-- - --- -.- - --_. ---- --.-
6.8
.938
.172
6.6
.803
0110
-.- 5 ~ 6
.485
.129
5.8 4. r
.500 .409
- .;.131_~_- -- ..1~1
'1.1
.631
.152
6.2
.537
.125
- - - -- ~ - ~
._--- - - .
) .-------- --PP'.1":BY 'VOLUME ~__n___._-
La. PER 1000 LB. OF FUEL
wEIG~T FLQW, LB./HR.
15.5
3.638
.424
?0;6' ---- 26~2--
4.164 4.387
.575 .693
.- -----.- ---"
--33~8-:----- 41.9 ---63~9-- -_u62.5-------62.8- --, 61-.5-----60.3----
'4.648 5.015 5.513 5.431 5.469 5.414 5.216
-------! ~5?-- .-- !.._~10 - - --_! .46_9____l;~2L___1 ~~~.8__~~22 \.213
:: J-
J-- -
\
~.- -.. -- -
-.. n_- ---
---- ----
00000 NOTES oo~oo, .
I.ALL EM)SSIONS CO~CENTRATtO~5 CORRECTED TO CONCENTRATIO~ IN WET EXHAUST FROM COMBuSTION WITH DRY AIR.
'2;E{)VIVALEt"CE RATIO CALCULATED FROM C02. CO. A"jD HC DATA AND FUEL COMPOSITION.':-- u----,-u U ,---------------- - ------
3~TOTAL ,NI'~OGEN OAIDES CALCULATED ~SING NOX CONCENTRATION AND MOLECULAR WEIGHT OF NOZ (46~01~.
-------
(' ---'--'- .----- - --- ---
EPA-AIRESEARCH EMISSIO~ PROGRA~ TEST SUMMARY
--- ------ ----:---0000000 OOOa-OOOOilOOOOa-oo 000000000 00000 0 0 000000 0 -
----- - ---.--
_._-------- --------
ENGINE
.r', ,
C... ----- FUEL H/C=r.990
OEiI PT.= 30.0
GTCP8S-129
SIN
P-34763
DATE OF TEST
4128/71
TYPE OF ~UEL
JP4
- ,RATED SHP= 160.0 RATED
SPECIFIC HU4IDITY= ~00357
(- POWER- SETTING NUMBER' - - om ----,"}- - , :HPLOAD\~G ONLY 16 20
PERCE~T~AX. COQRECTED POWER 0.0 26.0 50.0 74.3 98.5
. . (~- CORRECTED SrlAFT HP 0.0 -41.6 80.0 118.8 157.5
'Io4EASURED SHAFT' ~~ - -----------:0.0------ -'40.8"-----78.5 ,- 116.9, q- '155.2
EXHAUST GAS TEMP.. OEG.~ 530.0. 590.Q 655.0 735.0 850.0
( SHAFT SPEED, Nl. RPM " 41400.0' 41500.0 41400.0 41300.0 41200.0
. --'----CO'~PRESSORHH..ET TEMP.-.DEG.F -~---82.0 -,- 84.0--- - 84.0 .. 87.0' '" - 89.0
, COMPRESSOR oSCHG. PRES..PSIA ,
(, CORRECTED BLEED FLOW, L~/MIN 0.00 0.00 0.00 , 0.00
---:-CORRECTED FUEL FLOw, L8/HR - - 111.0-""- 129.0 --'7 - }it 8 . 0 . -'- 169.0
FA RATIO CALC. FROM EMISSION .0061 .0075 .0087 .0089
( , EQUIVALENCE RATIO' , .089 .111 .128 .130
---- OOiloooooooooooooooooooooooooa-ooooiloooooooooooa-OOOOSUMMARY OF REDUCED
CAR80N DIOXIDE "
(----, PERCENT'8Y' VOLUME'~--: "'1.22 "_m_-l~52'
'LB. C02 PER LB. OF FUEL 3.09 3.10
(:~ :--'----' wEIGHT FLO~...L~_,-/HR. - -,-.-- 34~_,-1,. ----~9q.6
-STOIC~IOMETRIC F/A= i06806
REL.HUMIDITY= ?3.0 PERCENT
EGT=1150.0 OEG.F RATED SPEED= 40700.0
AAROMETRIC PRESSURE=28.68 IN HGA
, COMBINATION SHP!BLEED LOADING
22 ' 19 15 - ' 9 -
~612 73~4 23,7 24.9
155.7 117.3 79.7 39.8
153.4 115.5 78.5 39~2
1250.0 12~0.0 1175.0 i130;0
40700.0 40860.0 40900.0 '40900~0
88.0-" 88.0 - --88.0-- '88.0
- 4
0.0
0.0
0.0-
1100.0
40900.0
86.0
0.00 58.12 79.68 88.84 98.34, 108.91
203.5 283.2 276.2 259.4 239.5 226.5
.0118 .0186 .0185 .0114 ~01i4 .0161
.174 .273 .272 .255 .241 .236
EMISSION DATAoooooooa-ooooooooooooOiloooooooooooooOOilOOOOilooooooo -
. . i
'1.77 --
3.10
45~.3
1.80
3.10
524.3
'2.39
3.11
633.7
3.75- 3.74 -- 3.50 3.31 h --- 3.24
3.13 3.13 3.13 3.12 3.12
886.1 8~4.0 810.7 74?3 706.2
-- -- - - -- -- -- -- - -- --.--- --
- -------_._--_.. -
-----, CARBON M0C40XIOE
'tI):o G) ,
t III '0 >-3 ' --
"1'0 I -- . PP'I BY VOLU~IE 149.2 172.8 181.0, 194.6' 187.5 130.1 138.4 160.8- ' 203.1 222.2 .
(D (D IX) . La. PER LB. 23.97':1 -- - 21.406 15.547 7.375 9.128 12.188
::J~' 1001) OF FUEL 22.349 '20.242 6.898 13.624
NO."" WEIGHT FLOW, La./HR. 2.662 2.883 2.996 3.618 3.164 1.954 2!037 2.368 2.919 3.086
4 UtI'" ~!,
)(- I ' - ------ -- -- ---. - --
:13 UN~'iJRt;Eu HY()~OCAR80NS PPM C4RRON
II' AS
(.----'- - . ------ PP~4 BY" VOLU:-IE ' , 43.5- -- 37.1 .--- 27.8' 22.9 12.7 2.1 '3.0 3.0 5.4 5.4
La. PER 1000 La. OF FUEL 3.992 2.744 1.-775 1.442 .601 .064 .092 .0913 .186 .190
C. ~' WEIGHT FLOw. Li3./HR. ,.443 .354 .21')3 .244 .122 .018 !025 .025 .045 .043
. , .- --.- -- ~ - _. - . . -- --- ---
NITRIC OXIDE
( --- --- -- ,- P"fo1 BY vOLU'IE '7.5 9.1 13.2 ' 17.3 24.9 61.8 - 59.3 51.6 44.5 41.5
LB. PER 1000 L8. OF, FUEL 1.296 1.254 1.579 2.039 2.216 3.510 3.383 3.138 2.858 2.729
(- WEIGHT F'LOW, L8./HR. .144 .162 .234 .345 .451 .994 !934 .814 .685 .618
NITROGEN DIOXIDE 1
(-- -- -- PPM BY VOLUME 13.8 13.5 14.2 15.4 15.2 9.5 9.4 11.6 14.0 14.9
LB. PER 1000 LB. OF FUEL 3.643 2.863 2.606 2.781 2.068 .824 .819 1.079 1 . 378' 1.499
( wEIGHT FLO~'h La oIHR. .404 .36Q .386 .470 .421 .233 !.226 ~280 .330 .340
TOUL OIl.IDES OF N ITROGE.\I AS N02 (3)
( - -- ----- PPM BY VOLUI<4E 21~3 22.5 27.4 32.7 40.1 7l.z 68.6 '63.2 58.4' 56.4
L8. PER 1000 LB. OF FUEL 5.630 4.786 5.027 5.906 5.466 6.205 6.005 5.890 5.760 5.683
.... WEIGHT FLOII. LB./HR. .625 ,.617 .. 744 .998 1.112 1.757 1!659 1.528 1.380 1.287
'~ ..
00000 NOTES 00000
(_.. I.ALL-EMISSIONS CO~CENTRATto~S CORRECTEn To CONCENTRA TI 0\1 IN WET EXHAUST FROM COMBUSTIOt-J WITH DRY oUR.
2~EQUIVALE"ICE RATIO CALCULATED FROI,', C02,CO. A~O HC DATA AND FUEL COMPOSITION.
3. TOTAL NIT~OGEf\I O"
-------
l )
,)
)
)-
. '1
')
)
)
)
ENGINE
GTC85-90
SIN
P-5786
FUEL H/C=I.f377
DEw PT.= 23.0
PROBE COMPARISON TEST
PROBE 1-10 vs PROBE 11-20
EPA-AIRESEARCH E~ISSION PROGRA~ TEST SUM~ARY
ooooooooooo~oooooo~oooooo~oooooooooooooooooo*o
DATE OF TtST ~/LB~?1 TYPE OF ~UEL JP5
STOICHIOMETRIC F/A= .06877
REL.HUMIDITY= 10.0 PEqCENT
RATED SHP= 0.0
SPECIFIC HU~IOITY=
PROBE LOCATIONS 1-10
POWER- SETTING NUMBER 1 ~ 3
PERCENT MA~. CORRECTED PO~ER 0.0 0.0 0.0
CORRECTED SHAFT HP 0.0 0.0 0.0
MEASURED SHAFT HP 0.0 O.J 0.0
EXHAUST GAS TEMP., DfG.F 565.0." 710.0 850.0
SHAFT SPEED. Nl, RP~ 41200.0 41100.0 40900.0
COMPRESSOR INLET TE~p..nEG.F 70.0 AO.O 80.0
COMPRESSO~ uSCHG. PRES.,PSIA 51.7 50.2 48.7
COR~ECTED BLEED FLOw, L3/MIN 0.00 43.41 68.80
CORRECTED FUEL FLO~ , L~/HR 107.9 139.2 104.2
FA ~ATIO CALC. FRO~ EMISSION .0075 .0101 .0123
EQUIVALENCE RATIO. .10Q .147 .179
ooooo~o~oooooooo*oooooooooooooo*o*****o***o*ooO*ooSUMMARY OF
CARBOrj OIOXIDE
PERCENT BY VOLU~E
LB. C02 PER L~. OF FUEL
WEIGHT FLOW, LB./HR.
1.49
3.05
329.2
.1 CARBON MO~O~IDE
, "" :J:I CO}
111> 'tI t-3
: I~ 'g ~ PPM BY vOLU~E 411i.9
, ~ ~ L~. PER 1000 L8. OF FUEL 54.460
:I~~~WEIGHT FLO:.J, LB./HR. 5.877
I ~~ - ~N8UR~E~ HYDROCARBONS AS PPM CARBON
1
'-)
...
"- -.:..-~--
PPi-1 BY VOlU-IE
lB. PER 1000 LB. OF ~UEL
WEIGHT FLOW, LB./HR.
NITR IC OXIDE
PPMBY vOlU'1E --
L8. PER 1000 LB. OF FUEL
W~IG~T FLOW, LB./HR.
t )-- ----
, NITROGEN DIOXIDE
: ) -- - ---
t) ------
~ )-----
) - _H
.L~-
-,
j--
PPM 8'1' VOLU~E
Ld. PER 1000 L~. OF FU~l
~~IGHT FLOW, lB./HR.
~OTAL OXIDES OF NIT~OGEN AS N02
PPM BY VOLU"1E.
LB. PER 1000 L8. OF FUEL
wEIGHT FLOW, LB./HR.
-. . - -. - ~-
144.3
10.724
1.157
3.5
.483
.052
- 11.8
2.520
.272
(3)
15.3 --
3.260
.352
2.03
3.09
430.6
419.5
40.004
5.652
55.6
3.075
.428
11.3
1.172
.163
13.7
2.179
.303
25.0-
3.'H6,
.55"3 "
- - - ---- ----"----
2.49
3.11
511.4
389.1
31.009
5.092
4
0.0
0.0
0.0
1000.0
40900.0
85.0
46.8
138.33
184.5
.0148
.215
REDUCED
3.00
3.13
577.7
321.8 -
21.738
4.011
RATED EGT=1170.0 DEG.F RATED SPEED= 40800.0
.00258 BAROMETRIC PRESSUPE=28.79 IN HGA
PROBE LOCATIONS 11-20
5 1 2 3 4 5
0.0 0.0 0.0 0.0 0.0 0.0
0.0 0.0 0.0 0.0 0.0 0.0
0.0 0.0 0.0 0.0 0;0 0.0
1170.0565.0 710.0 850.0 1000;0, 1170.0
40700.0 41200.0 41100.0- 40900.0 40AOO!0 40700.0
92.0 84.0 86.0 87.0 90!0 92iO
40.2 51.7 50.0 48.3 46.8 39.1
'109.!6 0.00 44.52 68.59 89.19 108.44
216.2 107.9 137!1 162.1 185.5 "211.0
.0181 .0071 .0097 .0119 .0143 .0166
.263 .103 .141 .173 .2ri9. r242
E~ISSION DATA~o~**oo*oooooooo**ooo*oo*oooo*ooooooo**o*ooo*.o...
3.66
3.14
6r9.4
1.96
3.09
42,+.2
2.92
3.13
581.4
3.38
3.14
663.4
- 11.5
1 .258
.232
- - 41.9
,4.562
.842
- ------ - -
1.40
3.04
32~.4
,2.41
3.12
505.2
- - ---.-- .
266.9
14.572
3.150 '
. '398.5
40.086
, 5! 496
364,0 . -
29.934
4.852
290.1
19.849
3.6e2.
231.8
13,714
2.894
405.7
55.956
6.038
18.2 4.4 4.5 157.7 55.3 16.6 -,- 4.8 -2.6---
.830 .167 .141 1"2.434 3.179 .779 .188' .088
.136 .031 .030 1.342 !436 .126 .035 .018
-- - --------
'20.2 30~3- 43.6 7.0 17.2 27.3 . 37.3 '44.2
1.728 2.155 2.550 1.031 1.856 2.402 2.735 2.804
.284 .398 .551 .111 !254 .389 .507 .592
.__.~ - ------ - - - ---- --- - --..--- _.~-- --- -- - - - --
8.5
.766
.r66
8 . 9 - ---, 7.; 9 ' -- - -,
1.469 1.065
!20! ;173'
6. 3- n.
,.610
.129
13.3
1.742
,286
33.5
4.391
.721
5.9
,660
.ll,2
9.0-
2.036
.220
--- ----- -.--
~ -- --- -----
_.-~-
------ ..---
- ---.--- -- -.
52.1
4.675
1.011
- 16.0 ----- 26.1
3.618 4.315
.390 !592
50.5-~
4.909
1.036
- --~- 35.1----. 43.2
- 4.748 4.853
'.770 .900 ' :
------- - ----- -
~- - --- - ------ ~~-- -- -- -~-- - - - - -
---,.--- -
---~- ----
*0*** NOTES ***0* . .
I.ALL E~ISSIONS CO~CE~TRATIO~S COR~ECTED TO CONCENTRATION IN WET EXHAUST FROM COMBUSTION WITH DRY AIR.
2.EQUIVALENCE RATIO CALCULI\TED FRO'A 'C02,CO, AND HC DATA AND FUEL COMPOSITION. --- -- - -- ~----------'----
3.TOfAL ~ITROr,E~ OXIDES CALCULATED USING NOX CONCENTRATION AND MOLECULAR WEIGHT OF N02 (46.01). '
-------
-------
{
SIN
P-24504
r
, t
. (
.I '
. i
341.5
5'0.806
0.000
. ..
(.
F:'PM 9Y VaLUME'" - . ,... ..'. .. -- - 58.0
LH. PER 1000 L8.aF FUEL 4.931
WEIGHT FLaw. L8./HR. 0.000
-.. +++ _.._--_.._-~-_..--- ~-
'NlT~IC .oXIDE
, (.._.. ,.
---- PPM ~Y -VOLUME'
. La. PER 1000 LB. OF FUEL
(-.--.- .-- ~~IGHTJLO~'. LRoIHR.
. NITROGEN DIOXIDE.
.,. -. -- 3 ~ 1
.497
0.000
( _.--
. - PPM 9Y vOLU~E --- ,-
LB. PER 1000 LB. OF FUEL
~EIGrlT FLOW, Lq./HR.
.. -'12~9
3.161
0.000
(..-
- -- --- -- - - ---
-.- - -- - --..
- -. - . ---
TOT~L OX[DES OF NITROGEN AS N02 (3)
(----- PPM BY.vOLUME' _... .d___- - '-'16.1--
l8. PER 1000 LB. .oF FUEL 3.924
~EIGHT FLaw, LB./HR. . 0.000
/
~---
EPA-AIRESEARC~ EMISSION PROGRAM TEST SU4MARY
~~_o~~oo,~~o*~~*~~**.*o**o*ooo**o.o*o*..*.oooo'
DATE OF T~ST 5/5/11 TYPE .oF FUEL .' JP4
429.9: -- 501.9
~7.75345.005
. '0.0000.000
. --- --+- .~. - --- .-
. 46.8 . --
2.972
0.000
.--- 6.2"
.743
0.000
14.3
2.618
0..000
20. (, .
3.751
0.000 .
36.9 ..
1.889
0.000
12.7
1.219
0.000
15.3
2.247
0.000
.. '27.9
4.115
0.000
. 2.68
3.08
0.0
498.0
36.410
0.000
.- - ~ -
24.5
1.023
0.000
. 20.7
1.625
0.000
13.7
1.645
0.000
34.4
4.136
0.000
---,- ---.--- .--
-----_..L.. ---'-+ ------.--.
--. .+ - . ------- ---
;
-------
----- ---..---- ---
. -----.---
--- -" .---
ENGINE GTC85-90-B
~ .
(....... ---------;. --FUEt--H/C=I.990 . STOIC~IO"1ETRIC F/A=' .06806' RATEOSHP= 0.0- .RATED E6T=1175.0 DEG.F RATED SPEED= 40800.0
'DEW PT.= 33.5 REL.HUMIDITY= ~3.0 PERCENT SPECIF[C HU~IOITY= .00418 8ARO~ET~[C PRESSURE~28.54 IN HGA
( ......:.....-.- POWER SETTING NUMBER' - - - - . - - 1 .- 2.-- -3-- 4 --_u_. --5 ---.d__- -- --- . ------
PERCENT M~X. CO~RECTEO POWER 0.0 ~.o 0.0, 0.0 0.0'
(' CORRECTED SHAfT Hi' . 0.0 0.0. 0.0 0.0 0.0
---~ MEASUREO SHAFT HP- -- ..---:----.- -"0.0--'-- - 0.0' .,- . 0.0 0.0'--~" 0.0
EX~AUST G~S TEMP.~ DEG.F 545.0 075.0; 825.0 975.0 1125.0
SHAFT SPEED, .Nl,RPM 40850.0 40760.0 140660.0 40580.0 40450.0
C.oI~PRESSOR INLET'TEi~P.,OEG.F'. . --77.0' . -,76.0' 81.0 . . .82.0 . -77.0 -----.-.-------.-------------.--
C.oMPRESSOR OSCHG. PRES.,PSIA 53.5 52.5.. 51.2 50.0 4Q.3
C CORRECTED BLEED FLOW, LB/MIN ~.OO 31.76 62.87. 83.95 101.34 .
---_:..- CORRECTED FUEL FLOW. .LB/rlR'- -. -- 0.0-'0.0' 0.0: 0.0 ""'0.0' --------..-------- ..---, ---- ------_.-- ------'----~
FA RATIO CALC. F~OM EMISSION .0065 .0088 .0109 .0134 .017-0
( . EQUIVALENCE RATIO' .096.129. .160 ..197. .250 . .
, ---'-'---o*ooo*o~o~~OOOOti)o G)-I CARSON ;-iONOX I DE
«P>:g~1 .
~CD c:, ,u PPM BY'V.oLUME - . -. . . ,-
N&~ La. PER 1000LS. .oF FUEL
«-oJ:< I' . -- ~1£IGHT FLOW. LB./HR.
tJ:I::I:I
. UN8URNEU rlYDROCARBONS AS PPM CAR80N
( -....:----. -
3.41
3.10
0.0
- - .-- .----+-- - --- -~-
--- ---~~-----
-- - - - --- - .
---- --"----- - - . -- --
. - - ---- -------.-
. ,
_._------~--_._----- -~.-
'~
... _._-- ----
419-.5
24.288
0.000
-- .---_._--~--- --- ----->
---- ---- --.
--- --- --<- - -----
-.---.--
- ---.-- --"._-----------~-...
6.3' --
.20B
0.000
-_._---+--- ~ ---
- .- ------.--... --
- - -- ---- -- -. ~ -- .--
-- + - - - - ~ -. -
30.6 .
1.899 .
0.000
_. - .- .
-------- -~.
12.6
1.197
0.000
43.2
4.108
0.000
~- -- .... - -".
~- - -..--. - .
+ - -. - -.
c-
00000 NOTES 0000* .
l.ALL EMISSIONS CO~CE~TRATrorjS CORRECTED TO CONCENTRAT[O~ IN WET EXHAUST FROM COMBUSTION WITH DRY AIR.
2.EQUIVALENCE RATIO CALCULATED FQO~ C02,CO. AND HC DATA AND FUEL COMP.oSITION.
J.TOTAL NITROGEN O~IOES CALCULATED IJSING NOX CONCENTRATION AND M.oLECUL~R WEIGHT OF N02 146.011.
-------
')
-}
-"
)
)
') - -.
')
: ~}
)-
)
I 'tI ~ C)
Jill '0 t-3
j~'g ~ .
" =' ~
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i 0:11-" ~
I >< I
tII~
,') .
L." -- -.-
',)
PROBE COMPARISON TEST
ENGII\JE
S/'JP- 24376
DATE OF TEST
EPA-AIRESEARCH EMISSInN PROGRA~ TEST SUMMARY
0000000000000000000000000000000000000000000000
JP-5
GTC65-90-B
FUEL H/C=I.92B
DEW PT.= 3&.0
STOICHIO~ETRIC F/A= .06843
REL.HUMIOITY= 9.0 PERCENT
RATED SHP= 0.0
SPECIFIC HU~IDITY=
PROBE LOCATIONS 1-10
POWER SETTING NUMBER 1 2 3
PERCE~T MAX. CORRECTED POWER 0.0 0.0 0.0
CORRECTED SHAFT HP 0.0 0.0 0.0
MEASURED SHAFT HP 0.0 0.0 0.0
EXHAUST GAS TE~p.. DEG.F 602.0 745.~ 900.0
SHAFT SPEED. Nl, RP~ 41200.0 41100.0 40800.0
COMPAESS0R INLET TEUP.,~EG.F 109.0 107.0 108.0
CO'1PRESSQR D.SC"'8. PRES. ,PSIA 49.2 47.3
CORRECTED HLEEO FLOW, LR/~IN 0.00 35.9~ 63.40
CORRECTED FUEL FLO~ , LB/HR 0.0 -0.0 -0.0
FA RATIO CALC. FRO~ EMISSION .0073 .009~ .0119
EQUIVALE~CE RATIO .107 .141 .173
ooooo*ooo*o**oooo*ooooo*ooooooo*o***ooo*oooooooOOOSU~MARY OF
CARROll' UIOXIDE
PERCEH BY VOLU-~E 1.47 1.93 2.38 2.93 3.38 1.47 . 1.90 2.39 2.99 3.45
LI"'. C02 PER LB. OF FUEL 3.07 3.08 3.09 3.11 3.12 3.07 3.08 3.09 3011 3.12
\.IE- 22.7 11.1 4.5 .6 .5 'l 15.3 8.6 -. c_. 1.8 . h. 8 n_____. .. U
Ltj. PER 1000 L9. OF FUEL 1 . 121 .645 .214 .023 .016 .205 X 10 .903 .404- .069 .026
"EIGHT FLOW, L6./HR. 0.000 0.000 0.000 0.000 0.000 .021 !115 ..063 .0,2 .005
- --- ~ ..
NI.TRIC OXIDE
C) - -- - --. . PPM BY. VOLU;~E
LB. PE~ 1000 L~. OF FUEL
f)_u_~ -- - ~~EIGHT FLOw, Lt3./HR.
i . .
: NITROGE~ DIOXIDE
:j.'-----
)-_.
) . -----
C:»llb/11
4
0.0
0.0
0..0
1052.0
40700.0
108.0
45.8
86.05
-0.0
.0145
.212
REDUCED
TYPE OF FUEL
RATED EGT=II&5.0 DEG.F RATED SPEED= 40500.0
.00461 BARO~ETRIC PRESSURE;28.70 IN HGA
PROBE LOCATIONS 11-20
5 1 2 3 4 5
0.0 0.0 0.0 0.0 0.0 0.0
0.0 0.0 0.0 0.0 O!O 0.0
0.0 0.0 0.0 0.0 0.0 0.0
1170.0 602.0 750.0 900.0 1050;0 1167.0
40500.0 41300.0 41100.0 40800.0 40600!0 40500.0
108.0 107.0 108.0 109.0 108.0 108.0
29.3 49.2 47.5 4&;0 29.3
101.07 0.00 36.25 &3.64 86.34 101.21
-0.0 101.0 127~0 157.0 119.0 198.0
.0168 .0~73 .0095 .0119 .01i8 .0171
.245 .107 .139 .174 .2"17 . .250
EMISSION DATAoooooooooooooooooooooooooooooooooooooooooooooooooo
8.4 12.7 11.3 25.2 34.0 13.6 - '11.8. 25.3 34.1 39.8-
1.195 1 .381 1.528 1.827 2.138 1.93~ 1.962 2.227 2.423 2.457
0.000 0-.000 0.000 0.000 0.000 .196 .!249 .350 .434 .486
-- - --- - -
8.1 11.2 11.9 11.5 - 9.4' 4.5-.----- 5.4 4.3..- . - 2.6 3.6
1.16& 1.860 1.&12 1.273 .911 .989 .914 .580 .280 ,345
0.000 0.000 0.000 .0.000 0.000 .100 ! 11 ~ .0~1 .050 .068
-------- --- ---- -- ------- n-_._- .- -+---
- PPH BY vOLt.J~'E
LB. PER 1000 LB. OF FUEL
wEIGHT FLOw, LB./HR.
----~ ----.-- -
TOTAL OXIDES OF NITROGEN AS N02
(31
PPM BY VOLUr~E 1&.5--.- .. 23.9 -
L8. PER 1000 LB. OF FUEL - 3.597 3.976;
)----____.~E~~'i_T_!:LO\ol' L~~J~~~ -----_.O.~O_O 0.000
29.2.
3.954
0.000
36.7
4.074
0.000
. - -..43.4
4.189
0.000
--18.1 -. - - 23.2--
3.961 '3.922
.400 .!.49a
_.- 29.6
3.994
.627
n_--:- 36.7 - ---43.5---------
. 3.995 4.112
.715 .814
.-- - - - --
-------
----~- ---------
)---
OOOO~ NOTES 00000 . .
I.ALL EMISSIO~S CONCE~TRATI0NS CORRECTED TO CONCENTRATIO~ IN WET EXHAUST F~O~ COMBUSTION .WITH DRY AIR.
2.E;"}UIVALE'4CE RATIO CALCULATED FRO'" C02,CO, AND.HC DATA AND FUEL COMPOSITION...- -- ----------- ------___L.
3.TOTAL NITROGEN ~~IDES CALCULATED USING NOX CONCENTRATION AND MOLECULAR WEIGHT OF N02 /46.01). .
----- ---- --- - - - ----- - -----
-------
~
AIRESEARCH MANUFACTURING CDMPANY DF ARIZDNA
A DIVIS'ON OF' THE: GARRETT CORPORATION
GROUP 4
LARGE AUXILIARY
POWER UNITS
-------
; - \- - - PROBE CCMPARISON TEST -.
- ( . . - -EPA-AIRESEARCH EI-IISSI.oN PR.oGRilM TEST SUMMARY
---,-- ---------:---- ---~-~-------_.- ---- ~it it~~ it it it it It tI tI ~tI tI tI tI tilt It It It It tI it It tlitit tI tilt It It It tilt It It It Itltil Olt 0
- ENGINE GTC85-90- B . S/"IP- 24376 DATE .oF T~ST ~/1?171 TYPE .oF ~UEL - JP-5
r - .
(.....--- f"UEL-.H/C=1.92ir - - STOICHI.oMETRIC F/A= --.06843 - RATED SHP=- 0.-0 - RATED
. - - DEW PT.= 36.0 REL.H1JMIDITY= 9.0 PERCENT SPECIFIC HtJ"1IDITy= .00461
( - .. . 12-POINT FIXED PROBE
- ~ POWER SETTING NUMBER -- - 1 - 2 . 3 -
PERCE"IT '1AX; CORRECTED POtiER 0.0 0.0 0.0
(. C.oRRECTEO SHAFT riP 0.0 0.0 0.0
. - -MEASURED SHAfT HP - -,- 0.0 '0.0 0.0
EXJ-fAUST G4S TEMP., OEG.f 605.0 742.0 900.0
( SHAfT SPEED, N1, RPM ,- 41300.0 41100.0 40900.0
r------CD"1PRESSOR- tNLEr TEIAP.,OEG;-F- '-104.0-- -106;0 '105.0 . --
CD~PRESSoR DSCHG. PRES.,PSIA 51.1 49.4 48.0
l: . CORREC TED BLEED FLOW, L>i/M I N' 0.0'0 35. B6 &2..40
- -- ---- -- CORREC TED FUEL FLOW , U.~/HR .- - 101.5 -121.0 -155.0
. FA RATIO CALC. FRO'~ E"MISSION .0072 . .0094. .0118
. <----- EQUIVALENCE RATID .106 .13a '.173
. otlootltllttlotltltltlo*Oittloo*ootlOittllttltttlOtlltlttltllttltltltltltltlltttOtltlSUMMARY OF
CARBON DIOXIDE
(- --- ---- PERCE\IT. BY -'vc)LU'.1E"- - ----.. ---.
L6. C02 PER LB. .oF FUEL
-'- ~_~EI_~.'iT FLOW, L8~~~~._---- ---------- .--
. -.------- _.. ---~ ----- -----
- - -------.
EGT=1165.0 DEG.F RATED SPEED= 40500.0
. BAR.oMETRIC PRESSURE=28.70 IN HGA
- 12-POINT MOVEABLE PROBE (LOCATIONS 1-2.0) .
5 - '~'-'--f ---- - -. ~ -, - 3 4 --5' .,
0.0 0." 0.0 0.0 0.0 0.0
0'.0 0.0 0.0 0.0 0.0 0.0
--- 0.0 - --n~o -0..0-----0;-0--------0.0 - -----(}.-O--
1156.0 602.0 750.0 900.0 1050.0 1161.0
40500.0 41300.0 41100.0 4d800.0, 40600.0 40500.0
105.0 .--107.0 --r08-.-0--109;O- --- r08~0-----108-;o---
43.& 1401 49.2 47.5 46.0 29.3
98.12 0.00 36.25. 63.&4 86.3~ 101.21
198._0 - --10i~(I---' --127.0----157;(j--~ -179;0------ f98~O----
.0167 .0013 .0095 .0119 .0148 .0171
.245 .107 .139 - .174 .217 .250 -.
EMISSION DATA~It*It**tI~tlo***o*tlotltltlo*tltltI*o~tltlOItOtlOtltl~tI~tllt!tltltltI*O!
'4 -
0.0 -
'0.0
----- 0.0 u-
1045.0
40700.0
105.0 -
46.5
83.63
-- 179.0
.0142 .
.20B
REDUCED
l.
-; )01 C)-l CARBON. I~ONO'( I DE
III '0'" I
C
-------
")
ENGli~E
GTCPfl61j-4
S/"
o -37596
~PA-AIRESEARCH EMISSION PROGPAM TEST SUMMARY
o*oooooooooOOO*~~Doooooooooooooo.oooo~*oo.oo.o
'"
, /
DaTE OF Tt.ST
5/2&/:1
TYPE OF FUEL
JPS
FUEL H/C=I.e17
DE>I PT.= 31.0
")
STOICHIOMETRIC F/A= .06871 qATED SHP= 300.0"
REL.HUMIDITY= 15.0 PERCENT SPECIFIC HU~IDITY=
SHP ONLY, SURGE VALVE OPEN
POWER SETTING NUMBER 1 & II 16
PERCENT MAX. CO~RECTED POwER 0.0 ?5.4 50.8 7h.l "
CORRECTED SHAFT HP 0.0 1&.\ 152.3 228.2
MEASURED SHAFT riP 0.0 14.9 150.1 224.9
EXHAU5T GAS TEMP.. DEG.F 681.0 123.0 163.0 801.0
SHAFT SPEED, Nl. RP~ 2~020.0 20n10.0 20010.0 20020.0
COMPRESSOR INLET TEMP..DF-G.F 86.0 A7.n 88.0 88.0
COMPRESSOR DSCHG. PRES..PSIA 55.1 55.1 56.2 56.8
CORRECTED HLEEO FLOW, L8/MJN 0.00 0.00 0.00 0.00
COR~ECT£D FuEL FLOw, Ld/HR 596.0 fl41.5 686.0 125.0
FA RATIu CALC. FROM EMISSION .0080 .0084 .0093 .0097
EQUIVALENCE RATIO .116 .122 .135 .140
ooo~~~~~~o~~*~~*~~o*~~o~~o~~*~~~*oo****~*o~****~~OSUMMARY OF qEoUCED
CARdO'~ OIOI(OE.
RATED EGT=1215.0 DEG.F RATED SPEED= 20000.0
.00313 8AROMETRIC Pw~SSURE=28.69 IN HGA
COMBINATION SHP/BLEED LOADING
20 22 19 15 10" 5 3
102.2 102.2 16.8 "50.1 25.3 0.0 0.0
306.5 306.6 2'0.3 " 152.1 15.8 0.0 0.0
302.3 302.4 221.3 150.1 14~9 0.0" 0.0
849.0 1209.0 1202.0 1194.0 1187.0 1180.0" 953.0
20010.0 20020.0" 20010.0 20010.0 20010;0 20020.020010.0"
89.0 89.0 90.0 90.0 92:0 92.0" 95.0",
57.1 51.1 50.5 49.4 48.0 46.9 49.6
0.00 468.46 483.82 504.98 524.23 541.12 432.06,
713.0 910.0 942.0 914.0 885.0 872.0 151.0
.0105 .0169 .0164 .0162 .0164 .0159 .0121
.}S3 .246 .238 .236 .238 .232 .184
EMISSION OATAOO~O~ooooo*o*o*o*oooooo~ooooooo~ooo.o*o.oo.o.ooo~o000000'
, ")
)
')
!
PERCENT IJY VOLU'1E 1.63 1.72 1.90 1.98 2.16 3.45 3.34 3.30 3.34 3.25" " 2.59 -
Ld. C02 PER LB. OF ~IJEL 3.14 3.14 3.14 3.15 3.15 3.15 3.15 3.15 3.15 3.15 3.15
wt.IGHT FLOW, L'3./HR. 1872.1 2010.3 215~.3 2281.2 2432.8 3057.0 29b8.0 2e8U.l 2787;7 2746.3 ?383.3
'tI>Q CARBON MONOXIDE
~'C~
'01 8Y 116.1 117.2 146.1 143.5 154.1 156.8 129.4 -
(I)(I)cx> PPM VOLU'~E 114.0 112.5 117.8 146.6
::s..... Lo. PER 1000 Lil. OF FUEL" 14.302 13.2<;5 12.341 11.384 10.945 8.52Q 8.817 8.106 9.2&0 9.681 10.016
"'11.'"
10"""'" Wt:!t>HT FLOW. La./IiR. 8.524 <;1.503 8.466 8.254 8.461 8.274 8!306 1.958 8.195 8.442 7.582-
)( I
I tII:G ,
UNRURNED HYDROCilRBO'liS AS PPM CARROII/ I
) " PPM BY VOLUME 11.2 9.6 9.4 8.5 9.3 12.3 10.0 13.0 - 11.8 '-:--13.4-
9.0
LEi. PER 1000 LB. OF FUEL .785 .635 .568 .494 .491 .299 .421 .341 .448 ,.411 I .592
,) wEIGHT FLOw, LB./HR. .468 .407 .389 .358 .380 .290 ~391 .317 .39& ,.364 ~_.' 4_~~
NITRIC OXIDE j- ~-
;,).- PP/1 8Y VOLUI.IE 18.4 20.6 22.3 24.E! 27.2 49.3 48.1 46.5 47.6 -- . 45.1 34.3--
LB. PER 1001) LB. Of FUEL 2.412 2.564 2.514 2,.661 '2.710' 3.074 3.133 3.026 3.068 2.983 ' 2.846
'. ) WEIGHT fLOw, LB oIHR. 1.437 1.645 1.724 1.929 2.095 2.981 2!952- 2.16& 2.715 2.601 2.154
r NITROGEN DIOXIDE
) PPfo1 BY VOLUME 5.2 5.4 5.9 5.8 - 6.1 8.8 8.2 8.5 -1~9 8.5- &~9-~
La. PER 1000 LB. Of fUEL 1.043 1.038 1.018 .970 .937 .831 .805 .848 .780 .862 .883
-) WEIGHT FLOw, LB./HR. .622 .666 .698 .703 ~724 .812 !758 .775 .6?0 .152 .668 '
- - --
TOTAL'OAIDES OF NITROGEN AS 'NQ2 (3)
)._- PPM"BY'VOLUME 23.5 26.1) "28.2 30.4 -- -- 33.4 58.1- 56.8" - - 55.0- 55.5 53.6" ---41 ; 3--
Lti. PI::R 1000 LB. OF FUEL 4.141 4.968. 4.872 5.0$00 5.092 5.549 5.609 5.481 5.483 5.435 5.246
~) \vEIGIiT FLOW, LB./HR. 2.826 3.181 3.342 3.661 3.936 ,5.383 5!283 5.015 4.853 4.740 3.971
-~-
00000 NOTI::S 00000
) - I.ALL EMISSIONS CO"JCE!'JTHATJrlNS CORRF.CH:o TO CONCEII/TRATIOt~ 1"1 WET EXHAUST fROM COMBUST! 011/ WITH DRY AIR.
' 2.EQUIVALENCE RATIO CALCULATED fR04 C02.CO, MID HC DATA AND FUEL COMPOSITION. --- - - - - - - --. ~ ~--- -----. -.- .---- -- _._~-
3.TOTAL NITROGEN OXIOES CALCULATED USING ,,/OX COt-;CENTRATION AII/O 40LECULAR WEIGHT Of 11/02 146.01>,'
,) -- - - -- --"- - -.---.- -. "'
-------
i::;.',t.: -""
(
,-" ,~. '. . ,,~
---------.-.-- ---- ---
EPA-AIRESEARCH E~ISSION PROGRA~ TEST SU~MARY
- --~----- -- .- ------*"OOOOOtHH.tHHtOO~«tttOOOfloO*OOOOO.H".O.oooooooooo~oo -
. ENGI~E GTCP&60-4 . SIN P-37705 OiTE OF TEST S/25/?1 TYPE OF EUEL JP5
C:-~-'FUEVI1/C=I;877 '--STOICHIO~1ETRIC F/A= .06877' RATED SHP=. 300.0 RATED EGT=1215.0 DEG.F 'RATED SPEED: 20000.0
DEw PT.="27.0 REL.HUMIDITY= 9.0 PERCENT SPECIFIC HU~IDITY= .00313 BAROMETRIC PRESSURE=28.5B IN HGA
" - (-- . - . SHP. Om. Y, ,SURGE VALVE OPEN . COMBINED SHP! BLEED LOADING
. POWER SETTING NUMBER 1 611 16 20 - 22' 19 .. 15 10 5' ,
. PERCENT M.X.. CORRECTED PO~ER 0.0 25.3 50.9 76.1 101.9 101.7 16.1 50.4 25.2 0.0
( . . CORRECTED S4AFT H~ '. 0.0 75.8 152.8 228.3 305.1 305.0 228.3 151.2 75.5 0.0
---:---'-MEASUKEO Sf1~FTrlP .-'-' , . 0.0" 7.4.9' '-'151.1' 225.9 '302.3 302.1 225..9 149.8 . 74;9 0.0'--
. EXHAUST ~AS TEMP.. DEG.F691.0 719.U 767.0 800.0 823.0' 1202.0 1192.0 1183.0 1112;0 1162.0
( . SHAFT SPEED. Nl. RP~ . 20010.0 20010.0 20000.0 20000.0 20010.0 20000.0 20000.0 20000.0 20000.0 20000.0
" -:-----COMPRES50R INLET'TE.'ip...OEG.-F' 9&.f}"--- - 96~'O"-: :-96.0-'-' "-97.0 '-96.0 98.0"'" 97.0 n 98.0 '. 100;0 .. 99.0
. . . COMPRESSOR DSCrlG. PRES..PSIA 54.1 54.7 55.3 56.0 56.6 51.0 49.9 48.7 47~3 46.0
. ( CORRECTED 8LEEO FLOW. L8/MIN 0.00 O.OQ' 0.00 0.00 0.00. 496.22 513.21 531.06' 555.n3 571.89
--.-- CORRECTED FUEL FLO' 'Ij 1-;3 I
.
-------
j
.,,) '0 1'3
I.Q '0 I
(1)(1)00
::1-.1
!AI Q. ... .
N""-.....:J
>< I
tJI:>:I
J
>.
ENGINE
TSCP100-'+
SIN
P-90122
DATE OF TEST
EPA-AIPESEARC~ EMI5510N PROGRAM TEST SUMMARY
*oooooooo*oo*oo~ooooooo~oooooooooooooooooooo..
;>.32
3-15
1060.6
78.7
6.790
2.288
58.4
2.881
.971
52.6
4.860
1.638
11.1
1.65~
.559
64.3
9.109
3.070
2.41
3015
116~.7
55.8
,+.630
I. "718
63.8
3.030
1.12'+
53.6
4.766
1.768
8.4
1.149
.426
62.0
8.456
3.137
5125/"!'1
STOIC~IOMETRIC F/A; .06817 RATED SHP; 142.0
REL.H1JJ.lIDITY;. 18.0 PERCENT SPECIFIC HU'~IDITV;
IDLE STANDBY MODE, SHP ONLY,
POWER SE.TTING NUMBER 1 2 " 11
PERCENT MAX. CORRECTED PO~ER 0.0 0.0 25.7 50.1
CORRECTED SHAFT H? 0.0 0.0 36.5 71.1
MEASUNE~ SH~FT HP 0.0. 0.0 36.0 10.7
EXHAUST GAS TEMP.. DEG.F 819.0 717.0 800.0 833.0
SHAFT S~EED. wi. RPM 176~O.0 24~90.0 25000.0 25hOO.O
SHAFT SPEED. N2. RPM ..3S350.0 35950.0 35830.0 35800.0
COMPRESSOR INLET TE~p..nEG.F 7d.0 89.0 92.0 99.0
COMPR[SSOR OSCHG. PRES..PSIA 6~.1 101.0 104.0 106.9
CORRECTED BLEED FLO~. L~/MI~ 0.00 0.00 0.00 0.00
CORRECTED FuEL FLOs . L8/HR 225.0 337.0 371.0 394.0
FA RATIO CALC. FR04 EMISSION .0113 .0113 .0118 .0122
EQIJIV"LENCE RATIO .164 .165 d71 .177
*****o*******o***************************o********SUM~ARV OF REOUCED
CARBOILUI0XIDE. .
2.28
3011
699.1
251.7
;>1.810
4.907
160.0
7.925
1.783
22.5
2.093
.471
12.9
1.833
.413
13)
35.4
5.042
1.134
2.50
3.15
1242.6
40.4
3.244
1.278
53.6
2.458
.968
62.8
5.396
2.126
&9.8
9.202
3.626
.--- ~ - - ----~- . - ---- ~----- - --- - --.--.------ - ---_.--..--.----~ ---- -,.--
~-_.- - ----~
FUEL i1/C;I.877
DEw PT.= 31.0
PERCE~T 8Y VOLU~E
L~. C02 PE~ LR. OF FUEL
WEIGHT fLO~. LA./HR.
CARRON I~OI~OX 1 DE
PPM RV VOLUME
L8. pER 1000 LB. OF FUEL
WEIGHT FLOw, LR./HR.
UNBURNEU HVDROCARBONS AS PPM CApqO~
PPM gv VOLUME
LB. PER 1000 LA. OF FUEL
WEIuHT FLOW. LB./HR.
NIT'!IC OXIDE
PP/1 BY vOLUME
LB. PER 1000 La. OF FUEL
WEIGHT FLOW. LB./HR.
NITROGEN DIoXIDE
PI'M RY VOLUME
Le. PER 1000 LB. OF FUEL
WEIGHT FLOw. LB./HR.
TOTAL OXIDEs OF NITROGEN AS N02
PPM BY VOLUME
LB. PER 1000 LR. OF FUEL
WEIGHT FLOW, LB./HR.
TYPE OF ~ UEL
JP5
I
') i
RATED EGT;1005.0 OF-G.F RATEQ SPEED= 35350.0 ~-.'I.
.00373 AA~O"'ETRtC PRESSUPE=Z8.66 IN HGA ,
SURGE VALVE OPEN NORMAL MODE, COMBI~TION LOAD MES
16 . 20 22 . 19 15 10 5 25
73.6 99. q 99.7 73.5 50.0 25.5 0.0 0.0 !
104.!) 141.9 141.& 104.4 71.0 3&.2 0.0. 0.0
104.0 141.0 1~9.6 102.8 69!8 35.5 0.0 0.0
858.0 '393.0 1005.0 1005.0 1005~0 - 1005.0. 1005.0 '887.0.
25900.0 2&400.0 27300.0 27300.0 27300!0 27300.0 :?7300.0 28100.0
35750.0 35690.~ 35350.0 35350.0 35350.0 35350.0 '15350.0 35350.0-
100.0 98.0 ~O.O 89.0 87.0 86.0 85.0 93.0
101'1.9 110.8 111.3 109...4.. 108!5 106.9 104.5 125.1
0.00 0.00 480.26 494.73 502.22 510.16, ~16.13 39i.08
417.5 442.0 495.5 487.0 477.0 469.0 467.0 461.0
.0127 .0135 .0152 .0152 .0152 .0153 .0155 .0130
. .185 .196 .221 .221 !22l .222' .226 .189
E~ISSION DATA**********************************************~******************.
2.60
3.15
1317.0
30.5
2.351
. .981
61.6
2.717
1 . 134
71.2
5.887
2.458
7.0
.928
.366
6.2
.781
.32&
2.77
3.1&
1394.9
25.0
1.812
.801
&0.5
2.511
1.110
72.8
5.663
2.503
16.5
1.965
.8&8
89.3
10.&48
4.70&
3.11
3.16
15t>4.t
23.8
1.537
!762
&5.5
2.421
1!200
97.5
6.754
3!347
3.8
.401
.! 199
101.3
10.755
5,!329
3.10
3.16
'153!.0
20.4
1.323
.644
15.3
2.786
1.351
109.3
7.578
3.691.
4.4 .
.4&8
.228
113.7
12.087
5.886
****0 NOTES *****
I.ALL £'1ISSIO~S CONCENTRATIONS CORRECTED TO CONCENTRATIO~ IN WET EXHAUST FROM COMBUSTION WIT~ DRY AIR.
2.EQUIVALE~CE RATIO CALCULATED FROM C02.CO.. ANO HC DATA AND FUEL COMPOSITION.
3.TOTAL NITROGEN OXIDES CALCULATED USING NOX CONCENTRA!ION AND MOLECULAR WEIGHT OF N02 146.01~.
17.4
9.807
4.094
3.10
3.16
150<;.7
20.4
1.323
.6~1
&9.6
.2.574
1.2;?8
90.8
6.291
3.004
3.5
.374
.1?9
94.3
10.029
4.784
- ---- -- -....,. - ~---:--._--- --- ----.---~---.- - . -- -- ---- --- --'.~ ----... -.
- --
3.12
3.16
147'1.8
3.18
3.16
147'+.5
22~7 22.6
1.458 1.431
.&84 - - ..668
81.5
2.995
1.405
95.7
6.594 I
.-3.093
4.0
.425
.199
62.3
2.253
1.052
92.1
6.237
2.913
3.5
.361
.168.
2.66
3.15
1472.8
26.1
1.972
.921 --
----- ---.
74.9
3.234
1.510
93.2
7.548
3.525-
5.7
.103
--..328-
-°99.71- 95.5 - -~~~
10.535. 9.924 12.214
4.941L~4~._~~:~~~~5~:= .
-- -_.__._---~
- -- _._--~ ~.~----
--.,.- --'.-.--
) I
-------
. I
, ;'c "
t.-,,".;-..-:....----- I . I
.:::;'".->,,: . f'
I
'~FlIEC f{/C:rl.B7:"c~'STOICHIOIAETRIC F/A= ~06a17 - RATEDSHP=142.0 RATED EGT=1005.0 DEG.F RATED SPEED= 35350.0 ,-- 'e) '['..
. OEW PT.= 33.0 REL.HUMIDITY:r 18.0 PERCENT SPECIFIC HUMIDITY= .00406 BARO~ETRIC PRESSURE=2B.72 IN HGA ,.,---- - -.,
, IDLE STANDBY MODE, SHP ONLY, SURGE VALVE OPEN' NORMAL MODE, COMBINATION LOAD MES ,
-'-:-POWER SETTING NUMBER ,-- 'I 2 6' 11 -. 16 20 22 19 15 10 5' 25
PERCENT M'X. CORRECTED POWER 0.0 ,O.~ 24.~ 48.573.3 99.6 99.8 73.5 49.9 25.5 0.0 0.0
CORRECTED SHAFT HP 0.0 0.0 34.8 68.9 104~0 141.5 141.8 104.4 70.9 36.2 0.0 0.0
--'MEASURED SHAFT .HP -- -- _d -- 0.0 - 0.0 34.8 68.4 - 103.9 141.1 1'+0.0 103.1 70;0 35.6 0.0 0.0,
.EXHAUST GAS TEMP.. DEG.F 842.0 939.0 979.0 884.0 929.0 956.0 1005.0 1005;0 1005~0 1005.0 1005.0 908.0
. ,SHAFT SPEED. N1. APM '17650.0 28100.0 27800.0 25550.0 26270.0 26750.0 27300.0 27300.0 27300.0 27300.0 27340.0 28100.0
---SHAFT SPEEO;N2, ~p.r~..'.n- ---'35440.0 35000.0. 34650.0 34650.0 ,35730.0 35720.0 35440.0 35440.0 35440~:0 35440.0. 35440.0 35440.,0 I
COMPRESSOR INLET TEMP..OEG.F. 82.0 100.0 103.0 96.0 102.0 100.0 89.0 . 89.0 89.0 87.0 87.0 91.0
COMPR£SSQR DSCHG. PRES..PSIA 5901 11501 114.0 102.1 106.1 110.1 109.8 108.6 107.9 ,104.4 102.6 116.5
CORRECTEO'BLEED FLO.., LB/MIN 0.00 0.00 0.00 0.00 0.00 0.00 448.74 464.48 474.14 488.92 477.35' 420.39 'i
CORRECTED FUEL FLOw, L8/HR 228.0 4Al.0 482.0 409.0 436.0 469.0 4~7.0 489.0 481.0" 471.0 460.0 414.0 .
FA RATIO CALC.'FROM EMISSIO~ .0116 .~140 .0146 .012t .0133 .0143 .0153 .0149 .0149 .0151 .0152 .0137 I
- -'--EGUIVAL,ENCE RATIO. , . '.168 .204 .212 ~ .185 '.193 ,".201 .223 . .216 !,211 ~220. .221 '.199 r
oooooooooooooooo~ooooooooooooooooooooooooooooooOOOSUMMARY OF REDUCED EMISSION DATAOOOOOO**oo*ooo*o*oooooooooooooooooooooooooooooo~oo0000000000000000:
CARBON DIOXIDE. , . ,I
- ..- -i~~c~ci~ ~i~~-~~~~F -~J~'L-- - . -~~-~~-- ~:~~ ~:~~ ~:~i' ---- -i:~~--- '--~:~i '~:~-:'" -. ~:~: ;':'~:'~:i:' ---~:~~ _.- - ~:~~ f
'---,--WEIGHT-LOW, LB./HR.' ~. 113~8 1520.2 1522.1 1292,8 1"311.2 -- 1481.8 15tl.l 1545.5 152~!2 1488.3145201 1491.8 ;
i --. - -, CARBON MONOX IDE
~06"~ ~-_. .- .- -. - .,-
'aI 'g c::.: PPM 91 vOLUME
~ ~; LB. PER 1000 L8. OF FUEL
~~~ : h' IIIEI6HT FLOW. LB./HR. .
, >< Ii'
0;1:0 i _.U_N"H.JHi'j~O ~.1I)ROCA~BONS AS PPM
ENGINE
TSCP700-4
PPM BY VOLU"'E
LB. PER 1000 LB. OF FUEL
WEIGH~ FLOW, LB./~R.
NITRIC OXIDE
- -. - -
----- -". --
PPM aY VOLUME
LB. PER 1000 L9. OF FUEL
wEIGHT FLOw. L8./HR~
NITROGEN DluXIDE
-- ~.- .
PPM 81 VOLUME
LB. PER 1000 LB. OF FUEL
WEIGHT FLOw, L9./HR.
TOTAL OXIDES OF ~ITROGE~AS NOZ
PPM 81 VOLU"'E
LB. PER 1000 LB. OF FUEL
wEIGHT FLOw. LB./HR.
SIN
P-90123
DIITE OF TEST
. EPA-AIRESEARCH'EMISSION PROGRAM TEST SUMMARY
-- o*.*oooooo*ooo*oo.oooooooooo**oooo~oooooo**~oo
16.0
1.111
.537
31.0
1.23>!
~595
45.?
3.3A5
1.6?'"
1.4
.156
.015
46.5
5.345
2.511
-- . -- -.". - -.
18.8
1.266
.610
55.6,
2.137-
1.030
46.5
3.353
1.616
2.1
.228
.110
48.6
5.368
2.581
5/2'7/11
22.2
1,.115
.701'
18.1
.799
.327,
44.6
3.6RS
1.507
3..1
.465
.190
48.3
60115
2.501
TYPE OF ~UEL
--- ...---- ~ --
18.9
1.391
'.607
. . -- ..
40.9
1.725
.752
52.1.
40111
1.195
2.8
.342
.149
54.9
6.654
?.901
14.8
1.018
.418
43.6
1.116
.805
60.4
4.452
2.088
3.3
.310
.173
63.7
1.195
3.314
jP-5
21.0
1.345
!668
24.5
.895
~445
83.1
5.742
2!854
.4
.042
~, 021
8401
8.846
4!396
- n.__._-.- ---
19.4
1.279
~625
31.4
1.186
.580
79.1
5.601
2.139
3.4
-.3.66
.179
82.5
8.954
4.318
**.00 NOTES 00000
I.ALL EMISSIONS CO~jCENTHATTnNS CORRECTf.~ To CO~CENTRATIO~ IN WET EXHAUST FROM COM8USTION WITH DRY AIR.
2.EQUIVALENCE RATIO CALcuLATED FRO" CO?.CO. AND HC OATA ANO FUEL COMPOSITION.
3.TOTAL NITROGEN OXIDES CALCULATED IISING NOX CONCENTRAT10N AND MOLECULAR WEIG~T OF N02 (46.011.
n_- ---- - .. -
193.2
16.351
3.7?8
CAPqON
69.5
3.361 .
.766
20.8
'1.
-------
APPENDIX C
I,
"
,
-------
~
AIRESEARCH MANUF"ACTURING CCMPANY CF" ARIZCNA
A. DIVISION OF" THE GARRETT CORPORATION
APPENDIX C
MEASURED AND CALCULATED EMISSIONS PERFORMANCE
PLOTTED AS A FUNCTION OF EQUIVALENCE RATIO
GT-8747-R
-------
~
AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A DIVISIDN Of" THE GARRETT CORPORATION
The curve index lists measured pollutant concentration in ppm,
calculated emissions index and formation rate and the corresponding
page number location for each.
CURVE INDEX
Appendix C Page Numbers
Measured
and
Calculated Performance
Group 1
propulsion
Units
Group 2
Small
APUs
Group 3
Medium
APUs
Group 4
Large
APUs
C02
% by volume
Ib/lb fuel
Ib/hr
1
2
3
19
20
21
38
39
40
57
58
59
CO
ppm by volume
Ib/lOOO Ib fuel
Ib/hr
HC (hot)
ppm by volume
Ib/lOOO Ib fuel
Ib/hr
4
5
6
22
23
24
41
42
43
60
61
62
7
8
9
25
26
27
44
45
46
63
64
65
NO
ppm by volume
Ib/lOOO Ib fuel
Ib/hr
10
11
12
28
29
30
47
48
49
66
67
68
NOx (as N02)
ppm by volume
Ib/lOOO Ib fuel
Ib/hr
13
14
15
31
32
33
50
51
52
69
70
71
Corrected shaft horsepower
16
34
53
72
Exhaust gas temperature
17
35
54
73
Corrected bleed flow
36
55
74
Corrected fuel flow
18
37
56
75
GT-8747-R
-------
~
AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A DIVISION DF' THE GARRETT CORPORATION
GROUP 1
AIRCRAFT PROPULSION ENGINES
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£ TSE231-1
+ TPE3311SlG
X TPE3311S1G
~ TPE331-43A
... T76-G-410
7305-2
2301-10
P-91165
P91168
P-611S7
GE00790
UNDERLINED SYMBOL
REPRESENTS GROUND
IDLE OPERATION
THEORETICAL CONVERSION
OF REACTANTS
I
I
I
I
N~
I
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/
/
wj
I
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wj
.- 1 I
0.14 0.16
EQUIV RATIO
, 1
0.18 0.20
FR/FA(STOIC. )
I
0.22
I
0.24
I
0.26
.-..
0.28
,
0.12
I
0.10
0.08
EPR / AIRESEARCH PROPULSION ENGINE EMISSION SUMMARY
i GT-8747--l
Appendix.. C
-------
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(!) TFE 731-2 7305-2
r- 40. TSE231-1 2301-10
+ TPE331151G P-91165
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A TSE231-1 2301-l0
+ TPE33ll5LG P-9ll65
X TPE33ll5LG P9ll68
~ TPE33l-43A P-6ll57
+ T76-G-410 GE00790
UNDERLINED SYMBOL
REPRESENTS GROUND
IDLE OPERATION
x :t
.!
"
731
~~
~.
+
231
x
7'P.E:/...
~.~76
.E:liT?.e..
--..OP.E:
x
x
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+
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0.14 0.16
EQUI V RRT 10
I ,
0.18 0.20
FR/FRCSTOIC. )
I
0.22
I
0.24
I
0.26
--,
0.28
0.08
0.10
EPR / RIRESERRCH PROPULSION ENGINE EMISSION SUMMRRY
GT-8747-R
Appendix C
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0.14 0.16
EQUIV RATIO
0.10
0.12
~ TfE 731-2 7305-2
A TSE231-1 2301-10
+ TPE331151G P-91165
X TPE331151G P91168
~ TPE331-43A P-61157
"" T76-cr410 GE00790
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Appendix C
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AIRESEARCH MANUFACTURING COMPANY OF ARIZONA
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Appendix C
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GT-8747-R
Appendix C
Page 48
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Appendix C
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Appendix C
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Appendix C
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~ Page 75
--,
-------
-------
EB
AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
/II.. DIVISION 0,. THE GARRETT CORPORATION
APPENDIX D
EXHAUST EMISSIONS STRATIFICATION
CURVES
GT-8747-R
-------
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AIRESEARCH MANUf"ACTURING COMPANY Of" ARIZONA
... DIVUIIDN Dr THE aAAAI:TT CORPQRATIDN
The emissions stratification curve index lists the engine model,
serial number, and the corresponding page numbers on which curves of
C02' CO, He (HOT), NO and NOx concentrations in ppm (except for C02
in mole. percent) are plotted as a function of sampling probe location
in the exit plane of the exhaust duct for lines of constant power set-
ting. Aiso, Figure 8 is included to show the probe number scheme and
location. Note that the "TEST NO." shown on each curve means the same
as power setting number as specified in Table 6 of this report.
CURVE INDEX
ENGINE MODEL
SiN
APPENDIX D
Group 1 Propulsion Enqines
Paqe Numbers
TFE731-2
TSE231-1
TPE331-1-151G
TPE331-1-151G
TPE331-43A
T76-G-410
7305-2
2301-10
P-91165
P-91168
P-61157
GE00790
1 through
6 through
11 through
16 through
21 through
26 through
5
10
15
20
25
30
Group 2 (Small APUs)
Paqe Numbers
GTCP30-92
GTCP30-92
GTCP36-6
GTCP36-6
p-28794
P-28794
P-34696
P-34772
31 through
36 through
41 through
46 through
35
40
45
50
Group 3 (Medium APUs)
GTCP85-180 P-567
GTCP85-180 P-507
GTCP85-180 P-518
GTCP85-180 P-595
GTCP85-180 P-593
GTCP85-98CK P-35648
GTCP85-98D P-27692
GTCP85-98D P-2 785 7
GTCP85-98 P-15454
GTCP85-98 P-15257
GTCP85-98 P-15541
GTCP85-115 P-18725
GTCP85-115 P-18781
GTCP85-115 P-18702
GTCP85-129 P-34763
GTC85-90 P-5786
GTC85-90B P-24504
GTC85-90B P-34276
Group 4 (Larqe APUs)
GTCP660-4 P-37596
GTCP660-4 p-37705
TSCP700-4 P-90122
TSCP700-4 P-90123
Paqe Numbers
51 through 55
56 through 60
61 through 65
66 through 70
71 through 75
76 through 80
81 through 85
86 through 90
91 through 95
96 through 100
101 through 105
106 through 110
. 111 through 115
116 through 120
121 through 125
126 through 130
131 through 135
136 through 140
Paqe Numbers
141 through 145
146 through 150
151 through 155
156 through 160
GT-8747-R
-------
~
AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A DIVISIDN 0" THt GAtl8cn CDRPQRATION
n,.
:\.
.. '~.....'...'. .
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('
t
'7
MP-30Z31
MOVABLE PROBE LOCATIONS AS ASSIGNED TO A
RADIAL CLOCK POSITION ILLUSTRATED ON A TPE331
ENGINE TEST SETUP
FIGURE 8
GT-8747-R
-------
~
AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A DIVISION OF" THE GARRETT CORPORATION
GROUP 1
AIRCRAFT PROPULSION ENGINES
-------
o
o
....
TEST NOaSYMBOL
1 C)
2 .6.
6 +
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16
20 ~
o
~
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o
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o
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1.00
I
2.00
I
3.00
I
4.00
I I
5.00 6.00
PROBE NO.
1-
7.00
1
8.00
I
9.00
I
10.00
TFE 731-2
SIN 7305-2
DEV. FUEL
AV.KEROS. DATE 6/10/71
CELL DENG
GT-8747-R
Appendix D
-------
o
Q
o
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Or')
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>-0
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6 +
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16
20 4>
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+
o
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6
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0 X X X X X
o X X
g
*
~ ~ ~ ~ ~ ~
01.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
TFE 731-2 SIN 7305-2 DEV. FUEL AV.KEROS. DATE 6/10/71 CELL DENG
GT-8747-R
Appendix D
-------
o
c::
0
~ TEST NO.SYMBOL
0 1 C)
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- 6 +
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1 1 X
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z
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00
a:::c::
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-------
o
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0
~ TEST NOaSYMBOL
4> 4> 1 C) 4>
o 4>
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C9 C9
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0
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
TFE 731-2 SIN 7305-2 DEV. FUEL AV.KEROS. DATE 6/10/71 CELL DENG
GT-8747-R
Appendix D
-------
o
~
0
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
TFE 731-2 SIN 7305-2 DEV. FUEL AV.KEROS. DATE 6/10/71 CELL DENG
GT-8747-R
Appendix D
-------
o
"!
v TEST NO.SYMBOL
1 C)
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1 1 X
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C? 20 ~
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1.00
I
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1
4.00
I I
5.00 6.00
PROBE NO.
I
7.00
I
8.00
I
9.00
I
10.00
TSE 231-1 SIN 2301-10
DEV
FUEL JP5 DRTE 6/24/71 CELL C106 D.P.2=FI
GT-8747-R
Appendix D
-------
o
C?
0
IX) TEST NOaSYMBOL
....
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C? 2 .6
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1.00
2.00
3.00
4.00
5.00 6.00
PROBE NO.
7.00
8.00
9.00
10 .00
TSE 231-1 SIN 2301-10 DEV FUEL JP5 DRTE 6/24/71 CELL C106 D.P.2=FI
GT-8747-R
Appendix D
-------
<:)
~
IX)
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v
v
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v + + +
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
TSE 231-1 SIN 2301-10 DEV FUEL JP5 DATE 6/24/71 CELL C106 D.P.2=FI
. GT-8747-R
Appendix D
-------
o
C?
0
... TEST NOaSYMBOL
c:-.o
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c:-.o
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
TSE 231-1 SIN 2301-10 DEV FUEL JP5 DRTE 6/24/71 CELL C106 D.P.2=FI
GT-B747-R
Appendix D
-------
o
C?
0
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1.00 2.00 3.00 4.00 ~O 6.00 7.00 8.00 9.00 1]).00
ROBE NO.
TSE 231-1 SIN 2301-10 DEV FUEL JP5 DATE 6/24/71 CELL C106 D.P.2=FI
GT-8747-R
Appendix D
-------
o
N
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v
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6 +
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16 ~
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1.00
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3.00
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4.00
I I
5.00 6.00
PROBE NO.
I
7.00
I
8.00
I
9.00
I
10.00
TPE331-1-151G S/NP91165 O/H FUEL AV1R KERO DRTE 6/1/71 CELL C-103
GT-8747-R
Appendix D
-------
o
C?
0
IX> TEST NOoSYMBOL
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-------
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CO TEST NOaSYMBOL
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
TPE331-1-151G S/NP91165 O/H FUEL AV1A KERO DATE 6/1/71 CELL C-103
GT-8747-R
Appendix D
-------
o
~
<0 TEST NOo5YMBOL
C»
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to
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5.00 6.00
PROBE NO.
I
7.00
I
8.00
I
9.00
I
lO.OO
TPE331-1-151G S/NP91165 O/H FUEL AV1A KERO DATE 6/1/71 CELL C-103
GT-8747-R
Appendix D
-------
a
~
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1.00
2.00
3.00
4.00
5.00 . 6.00
PROBE NO.
7.00
8.00
9.00
~
10.00
TPE331-1-151G SIN P91168 O/H FUEL AV1A KERb DATE 4/30/71 CELL 105
GT-8747-R
J\ppendix D
-------
o
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 LO.OO
PROBE NO.
TPE33~1-151G SIN P91168 O/H FUEL RV1R.KERO DRTE 4/30/71 CELL 105
~T-8747-R
Appendix D
-------
o
~
0
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N
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
TPE33~1-151G SIN P91168 O/H FUEL AV1A KERO DATE 4/30/71 CELL 105
GT-8747-R
Appendix D
-------
o
o
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TEST NOasYMBOL
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2 6
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PROBE NO.
I
7.00
~
8.00
2.00
3.00
4.00
X
+
~
C9
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9.00
TPE33~1-151G SIN P91168
O/H FUEL AV1A KERO DATE 4/30/71 CELL 105
GT-8747-R
Appendix D
Page 20
x
+
~
C9
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-------
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2.00
3.00
4.00
5.00 6.00
PROBE NO.
7.00
8.00
9.00
---,
10.00
TPE331-43A SIN P61157 O/H FUEL JP5
DATE 5/11/71 CELL-103
GT-8747-R
Appendix D
-------
o
C?
0
(X) TEST NOQSYMBOL
...
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
TPE331-43A SIN P61157 O/H FUEL JP5 DATE 5/11/71 CELL-103
GT-8747-R
Appendix D
-------
o
~
0
v TEST NO.SYMBOL
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
TPE331-43R SIN P61157 O/H FUEL JP5 DRTE 5/11/71 CELL-103
GT-8747-R
Appendix D
-------
o
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
TPE331-43A SIN P61157 O/H FUEL JP5 DATE 5/11/71 CELL-103
GT-8747-R
Appendix D
-------
o
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o +
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PROBE NO.
TPE331-43A SIN P61157 O/H FUEL JP5 DATE 5/11/71 CELL-103
GT-8747-R
Appendix D
-------
a
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PROBE NO.
T76-G-410 SIN GE 00790 O/H FUEL JP5 DATE 5/6/71 CELL 104
GT-8747-R
Appendix D
-------
o
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0
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
T76-G-410 SIN GE 00790 O/H FUEL JP5
GT-8747-R
Appendix D
Page 28
-------
o
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PROBE NO.
T76-8-410 SIN GE 00790 O/H FUEL JP5 DRTE 5/6/71 CELL 104
GT-8747-R
Appendix D
-------
~
AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A DIVISION Of" THE GARRETT CORPORATION
GROUP 2
SMALL AUXILIARY
POWER UNITS
-------
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5.00 6.00
PROBE NO.
I
7.00
I .
8.00
I
9.00
I
10.00
GTCP30-92 (RTOM) SIN P-28794. FUEL RV.KEROSINE oRTE 5/17/71 CELL 0-110
GT-8747-R
Appendix D .
-------
o
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5.00 6.00
PROBE NO.
I
7.00
I
8.00
I
9.00
---.
10.00
GTCP30-92 (ATOM) SIN P-28794. FUEL AV.KEROSINE DATE 5/17/71 CELL 0-110
GT-8747-R
Appendix D
-------
o
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PROBE NO.
GTCP30-92 (RTOM) SIN P-28794. FUEL RV.KEROSINE DRTE 5/17/71 CELL 0-11 0
GT-8747-R
. Appendix D
-------
o
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PROBE NO.
GTCP30-92 (ATOM) SIN P-28794. FUEL AV.KEROSINE DATE 5/17/71 CELL 0-110
GT-8747-R
Appendix D
-------
o
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1.00
2.00
3.00
4.00
5.00 6.00
PROBE NO.
7.00
8.00
9.00
10.00
GTCP30-92 (RTOM) SIN P-28794. FUEL RV.KEROSINE DRTE 5/17/71 CELL 0-110
GT-8747-R
. Appendix D
-------
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PROBE NO.
GTCP30-92 (VAP) SIN P-28794, O/H, FUEL AV.KEROS.,OATE 5/18/MU
GT-8747-R
Appendix D
-------
a
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PROBE NO.
GTCP30-92 (VRPJ SIN P-28794, O/H. FUEL RV.KEROS.,DRTE 5/18/MU
GT-8747-R
Appendix .D
-------
o
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5.00 6.00
PROBE NO.
I
7.00
I
8.00
I
9.00
--,
10.00
GTCP30-92 (VAP) SIN P-28794, O/H, FUEL AV.KEROS.,OATE 5/18/MU
GT-8747-R
Appendix D
-------
a
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PROBE NO.
GTCP30-92 (VAP) SIN P-28794, O/H, FUEL AV.KEROS.,OATE 5/18/MU
GT-8747-R
Appendix D
-------
a
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5.00 6.00
PROBE NO.
GTCP36-6 ,SIN P-34696, O/H. FUEL JP5
DATE 5/14/71
CELL C-102
GT-8747-R
Appendix D
-------
o
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
GTCP36-6 .S/N P-34696. O/H. FUEL JP5 DRTE 5/14/71 CELL C-102
GT-874 7-R
Appendix D
-------
c_,
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PROBE NO.
GTCP36-6 ,SIN P-34696, OIH, FUEL JP5 DATE 5/14/71 CELL C-102
GT-8747-R
Appendix D
-------
o
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PROSE NO.
GTCP36-6 .S/N P-34696. O/H. FUEL JP5 DRTE 5/14/71 CELL C-102
GT-8747-R
Appendix D
-------
o
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PROBE NO.
GTCP36-6 .S/N P-34696. O/H. FUEL JP5 DRTE 5/14/71 CELL C-102
GT-8747-R
Appendix D
-------
o
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4.00
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5.00 6.00
PROBE NO.
I
7.00
I
8.00
I
9.00
I
10.00
GTCP36-6. SIN P-34772. O/H. FUEL JP5
ORTE 5/14/71
CELL 0-115
GT-8747-R
Appendix D
-------
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
GTCP36-6. SIN P-34772. O/H. FUEL JP5 DATE 5/14/71 CELL 0-115
GT-8747-R
Appendix D
-------
a
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
GTCP36-6. SIN P-34772. O/H. FUEL JP5 ORTE 5/14/71 CELL 0-115
GT-8747-R
Appendix D
-------
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
GTCP36-6. SIN P-34772. O/H. FUEL JP5 DRTE 5/14/71 CELL 0-115
GT-8747-R
Appendix D
-------
~
AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
lit DIVISION OF THE GARRETT CORPORATION
GROUP 3
MEDIUM-SIZE
AUXILIARY POWER UNITS
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PROBE NO.
GTCP85-180(98CK) SIN p-567 PROD. FUEL RV.KEROS. DATE 6/14/71 CELL 0-111
GT-8747-R
Appendix D
-------
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PROBE NO.
GTCP85-180(98CK) SIN P-567 PROD. FUEL AV.KEROS. DATE 6/14/71 CELL 0-111
GT-B747-R
Appendix D
-------
o
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3.00
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5.00 6.00
PROBE NO.
I
7.00
I
8.00
I
9.00
---,
10.00
GTCP85-180(98CK) SIN P-567 PROD. FUEL RV.KEROS. DRTE 6/14/71 CELL 0-111
GT-8747-R
. Appendix D
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PROBE NO.
GTCP85-180(98CKJ SIN P-567 PROD. FUEL RV.KEROS. DRTE 6/14/71 CELL 0-111
GT-8747-R
Appendix D
-------
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10.00
2.00
3.00
4.00
5.00 6.00
PROBE NO.
7.00
8.00
GTCP8S-180(98CK) S/NP-S07 PROD. FUEL, RV. KERO DRTE 6/14/71,CELLD-lll
GT-8747'&R
Appendix D
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PROBE NO.
GTCP85-180(98CK) S/NP-507 PROD. FUEL. AV. KERO DATE 6/14/71.CELLD-ll1
GT-8747-R
Appendix D
-------
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PROBE NO.
GTCP85-180(98CKJ S/NP-507 PROD. FUEL, RV. KERO DRTE 6/14/71,CELLD-l11
GT-8747-R
Appendix D
-------
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PROBE NO.
GTCP85-180(98CK) S/NP-507 PROD. FUEL, AV. KERO DATE 6/14/71,CELLD-lll
GT-87 4 7-R
Appendix D
-------
o
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5.00 6.00
PROBE NO.
7.00
8.00
9.00
10.00
GTCP85-180 SIN P-518 PROD. FUEL RVK. DRTE 6/15/71
GT-8747-R
Appendix D
'Page 61
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3.00
4.00
5.00 6.00
PROBE NO.
7.00
8.00
9.00
10.00
GTCP85-180 SIN P-518 PROD. FUEL AVK. DATE 6/15/71
GT-8747-R
Appendix D
Page 62
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PROBE NO.
GTCP85-180 SIN P-518 PROD. FUEL RVK. DRTE 6/15/71 CELL 0-111
GT-8747-R
Appendix D
-------
o
C?
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1.00
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4.00
5.00 6.00
PROBE NO.
7.00
8.00
9.00
10.00
GTCP85-180 SIN P-518 PROD. FUEL RVK. DRTE 6/15/71
GT-8747-R
Appendix 0
Page 64
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7.00
8.00
9.00
~
10.00
GTCP85-180 DIN P-595 FUEL RVK .PROD.
DRTE 6/15/71
CELL 0-111
GT-8747-R
Appendix D
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PROBE NO.
GTCP85-180 DIN p-595 FUEL AVK ,PROD. DATE 6/15/71
GT-8747-R
Appendix D
Page 68
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C? +
~ + +
+ + + + +
0 L!:I. L!:I. L!:I. L!:I. L!:I. L!:I.
C? L!:I. L!:I. L!:I.
o C9
- C9
C9 C9 C9 C9 C9 C9
C9
o
C?
lJ)
+
o
0 --
o
1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
GTCP85-180 DIN P-595 FUEL RVK .PROD. DRTE 6/15/71 CELL 0-111
GT-8747-R
Appendix D
-------
a
C?
tD TEST NO.SYMBOL
en
1 C)
a 6 ~
C?
a:> 1 1
a:> +
16 X
a 20 0
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r- 5
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a
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tD
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a
C? C)
a:>
+
a
a
a
\.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
GTCP85-180 DIN P-595 FUEL RVK ,PROD. DRTE 6/15/71 CELL 0-111
GT-8747-R
Appendix D
-------
a
CD
.,.
a
N
.....
*
~
~
~
it
,
TEST NO.SYMBOL
1 C)
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16 X
20
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a
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+ + + + +
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a Jh Jh Jh Jh Jh Jh
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a
~
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a
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a
a
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o
a
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I
8.00
I
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4.00
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5.00 6.00
PROBE NO.
GTCP85-180 P-593 PROD. FUEL AVK. DATE 6/16/71 CELL 0-111
GT-8747-R
Appendix D
-------
o
~
0
CO TEST NOaSYMBOL
~
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~
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C9 C9 C9 C9 C9 C9 C9
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~
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0
~
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~
o
o
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1.00
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2.00 3.00
I
4.00
I -~
5.00 6.00
PROBE NO.
I
7.00
I
8.00
I
9.00
~
10.00
GTCP8S-180 P-S93 PROD. FUEL RVK. DRTE 6/16/71 CELL 0-111
GT-8747-R
Appendix D
-------
o
C?
~ TEST NO.SYMBOL
-
1 C)
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- .
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)(
0
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1 .00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
GTCP8S-180 P-S93 PROD. FUEL AVK. DATE 6/16/71 CELL 0-111
GT-8747-R
Appendix D
-------
o
C?
0
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+
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o
C?
If)
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
GTCP85-180 P-593 PROD. FUEL RVK. DRTE 6/16/71 CELL 0-111
GT-8747-R
Appendix D
-------
o
~
0- TEST NO.SYMBOL
CD
~ .q>
.q> 1 (1) .q>
0 )<: z )<: 6 6
C?
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.q> z , 16)!{ X
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:z~ A A A
A
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N C9 C9 C9
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o
C?
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o
o
OJ)
o
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o
1.00
2.00
I
3.00
I
4.00
I I
5.00 6.00
PROBE NO.
I
7.00
I
8.00
I
9.00
1-
10.00
GTCP8S-180 P-S93 PROD. FUEL AVK.
DATE 6/16/71 CELL 0-111
GT-8747-R
Appendix D
-------
o
"'!
U) TEST NOoSYMBOL
1 0
0 6 ~
rl:!
... 1 1 +
16 X
0 20
"; 22 4>
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19 :x:
y 15 Z
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C) C) C) C) C) C) C) C)
C)
0
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-
°
CD
o
o
....
o
1.00
2.00
- I
3.00
- I
4.00
I I
5.00 6.00
PROBE NO.
I
7.00
I
8.00
I
9.00
---,
10.00
GTCP85-98CK SIN P-35648,0/H,FUEL RV.KEROS.ORTE 6/7/71 C-101
GT-8747-R
Appendix D
-------
o
C?
0
r- TEST NO.SYMBOL
N
0 1 (')
C? 6 .6
0
co 1 1 +
N
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s + 6 6 6 6 6
~ + + C) C) C) ~ C)
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C!
0
~ I I I I I I I I --,
1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
GTCP85-98CK SIN P-35648,0/H,FUEL RV.KEROS.ORTE 6/7/71 C-101
GT-8747-R
Appendix D
-------
o
C?
CD
<:'>J TEST NO.SYMBOL
1 C)
0 C) 6 6
C?
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16 X
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v
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1.00
,
2.00
I
3.00
I
4.00
I I
5.00 6.00
PROBE NO.
I
7.00
- I
8.00
I
9.00
--,
10.00
GTCP85-98CK SIN P-35648.0/H.FUEL RV.KEROS.ORTE 6/7/71 C-101
GT-8747-R
Appendix D
-------
o
c:
ex:> TEST NOoSYMBOL
...
1 (!)
0 6 .6
c:
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16 X
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c:
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2.00
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7.00 8.00 9.00 10.00
I
4.00
I I
5.00 6.00
PROBE NO.
GTCP85-98CK SIN P-35648,O/H.FUEL RVoKEROS.DRTE 6/7/71 C-101
GT-8747-R
Appendix D
-------
C)
~
<:-J TEST NOaSYMBOL
IJ)
1 C)
C) 6 6
~
0::> 1 1 +
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16 X
C) ~ z 20 <'>
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1.00
I
2.00
I
3.00
I
4.00
I I
5.00 6.00
PROBE NO.
I
7.00
I
8.00
I
9.00
----,
10.00
,
GTCP85-98CK SIN P-35648,0/H,FUEL RV.KEROS.ORTE 6/7/71 C-101
GT-8747-R
Appendix D
-------
o
C'!
IJ) TEST NO.SYMBOL
1 C)
0 6 ~
CI?
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16 X
0 20 0
~ 22 zt
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19 x:
y y y 15 z Z y y
o Z 10 4> Y 4>
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o ):!( )!( )!( )!( )!( )!(
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+ + + + + + + +
o
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C) C) C) C)
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o
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o
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1.00
I
2.00
I
3.00
I
4.00
I I
5.00 6.00
PROBE NO.
I
7.00
1
8.00
I
9.00
---,
lO.OO
GTCP85-98D. SIN P-27692. O/H. FUEL JP5, DRTE 5/3/71 CELL NO.D-111
GT-8747-R
Appendix D
-------
o
C?
0
....
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0 1 12)
C? 6 6
0
N
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16 X
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C?
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C?
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
GTCP85-98o. SIN P-27692. O/H. FUEL JP5. oRTE 5/3/71 CELL NO .0-111
GT-8747-R
Appendix D
-------
o
C?
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N
1 Q)
0 6 6
C?
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N
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o
l.OO 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
GTCP85-98D. SIN P-27692. O/H. FUEL JP5. DATE 5/3/71 CELL NO.D-111
GT-8747-R
Appendix D
-------
o
~
o
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...
o
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o
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o
~
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o
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1.00
.
4.00
. -.
5.00 6.00
PROBE NO.
.
2.00
.
3.00
TEST NO.SYMBOL
1 C)
6 ~
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16 X
20 ~
22 4-
19 x:
15 Z
10 Y
5 ~
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7.00
--G
8.00
-0-----'
9.00 10.00
GTCP85-98D. SIN P-27692. O/H. FUEL JP5. DRTE 5/3/71 CELL NO.D-111
GT-B747-R
Appendix D
-------
o
0
1.0 TEST NO.SYMBOL
t3)
1 C)
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C?
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1.0
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1.00
2.00
I
3.00
I
4.00
I I
5.00 6.00
PROBE NO.
- ,
7.00
I
8.00
I
9.00
)j{
10.00
GTCP85-98D. SIN P-27692. O/H. FUEL JP5. DRTE 5/3/71 CEll NO.D-11l
GT-8747-R
Appendix D
-------
a
~
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1 C)
a 6 6
~
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N
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1.00
I
3.00
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4.00
I I
5.00 6.00
PROBE NO.
I
7.00
- I
8.00
I
9.00
------,
10.00
2.00
GTCP85-980
SIN P-27857 FUEL. JP-5 DRTE. 5/6/71
GT-8747-R
Appendix D
Page 86
-------
o
C!
0
(X) TEST NO.SYMBOL
"
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to
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3.00
I
4.00
I I
5.00 6.00
PROBE NO.
----.-
7.00
I
8.00
I
9.00
----,
10.00
GTCP85-98D
SIN P-27857 FUEL. JP-5 DATE. 5/6/71
GT-8747-R
Appendix D
Page 87
-------
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PROBE NO.
GTCP85-98D SIN P-27857 FUEL. JP-S DRTE. 5/6/71 CELL 0-113
GT-8747-R
Appendix D
-------
o
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PROBE NO.
GTCP85-980 SIN P-27857 FUEL. JP-5 ORTE. 5/6/71 CELL 0-113
GT-8747-R
Appendix D .
-------
o
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I
7.00
I
8.00
I
9.00
---,
10.00
GTCP85-98D
SIN P-27857 FUEL. JP-5 DRTE. 5/6/71
GT-8747-R
Appendix D
Page 90
-------
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I
7.00
I
8.00
I
9.00
n--,
10.00
GTCP85-98 .S/N P-15454. O/H. FUEL JP5. DATE 5/17/71
GT-8747-R
Appendix D
Page 91
-------
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PROBE NO.
". O/H. FUEL JP5,
GTCP85-98 .S/N P-15454. DATE 5/17/71 CELL 0-111
GT-8747-R
Appendix D
-------
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PROBE NO.
GTCP8S-98 ,SIN P-1S4S4, O/H, FUEL JPS, oRTE sin 171 CELL 0-111
GT-8747-R
Appendix D
-------
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PROBE NO.
GTCP85-98 ,SIN P-15454, O/H, FUEL JP5, DATE 5/17/71 CELL 0-111
GT-8747-R
Appendix D
-------
a
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PROBE NO.
GTCP85-98 .S/N P-15454. O/H. FUEL JP5. DRTE 5/17/71 CELL 0-111
GT-B747-R
Appendix D
-------
o
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I
7.00
- I
8.00
I
9.00
---,
lO.OO
GTCP85-98. SIN P-15257. O/H. FUEL AV.KEROS. DATE 5/18/71 CELL C-101
GT-8747-R
- Appendix D
-------
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C?
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PROBE NO.
GTCP85-98. SIN P-15257. O/H. FUEL AV.KEROS. DATE 5/18/71 CELL C-101
GT-8747-R
Appendix D
-------
(T)
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. PROBE NO.
GTCP85-98. SIN P-15257. O/H. FUEL AV.KEROS. DATE 5/18/71 CELL C-l01
GT-8747-R
Appendix D
-------
o
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PROBE NO.
GTCP85-98. SIN P-15257. O/H. FUEL AV.KEROS. DATE 5/18/71 CELL C-101
GT-8747-R
Appendix D
-------
CJ
c:
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PROBE NO.
GTCP85-98. S/N P-15257. O/H. FUEL RV.KEROS. DRTE 5/18/71 CELL C-101
GT-8747-R
Appendix D
-------
o
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7.00
I
8.00
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9.00
I
10.00
GTCP85-98. SIN P-15541. O/H. FUEL AV.KEROSINE. DATE 5/21/71 CELL 0-111
GT-8747-R
Appendix D
-------
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c::>
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,
lO.OO
GTCP85-98. SIN P-15541. O/H. FUEL AV.KEROSINE. DATE 5/21/71 CELL 0-111
GT-8747-R
Appendix D
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PROBE NO.
GTCP85-98. SIN P-15541. O/H. FUEL AV.KEROSINE. DATE 5/21/71 CELL 0-111
GT-8747-R
Appendix D
-------
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PROBE NO.
GTCP85-98. SIN P-15541. O/H. FUEL AV.KEROSINE. DATE 5/21/71 CELL 0-111
GT-8747-R
Appendix D
-------
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5.00 6.00
PROBE NO.
I
7.00
GTCP85-115 SIN P-18725 ,O/H, FUEL JP5 DATE 5/13/71
GT-8747-R
Appendix D
Page J,~6
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
GTCP85-115 SIN P-18725 .O/H. FUEL JP5 DATE 5/13/71 CELL 0:-115
GT-8747-R
Appendix D
-------
o
C?
'" TEST
N NO.SYMBOL
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C?
N
N 1 1 +
16 X
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C?
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
GTCP85-115 SIN P-18725 ,O/H. FUEL JP5 oRTE 5/13/71 CELL 0-115
GT-8747-R
Appendix D
-------
o
CO?
iJ) TEST NO.SYMBOL
u:>
1 C9
0 6 6
0
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16 X
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C? .(j) (j) (j)
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1.00 2.00 3.00 4.00 5.00 6.00 9.00 10.00
PROBE NO.
GTCP85-115 SIN P-18725 ,O/H, FUEL JP5 DRTE 5/13/71 CELL 0-115
GT-8747-R
Appendix D
-------
o
C?
0 TEST NO.SYMBOL
r-
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
GTCP85-115 SIN P-18725 ,O/H, FUEL JP5 oRTE 5/13/71 CELL 0-115
GT-8747-R
Appendix D
-------
a
~
U) TEST NO.SYMBOL
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a
a
-------
o
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0
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(r)
0 1 8
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0
N 1 1 +
(r)
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PROBE NO.
GTCP85-115 SIN P-18781 O/H. FUEL RV.KEROS. oRTE 6/8/71 CELL 0-111
GT-8747-R
Appendix D
-------
o
~
.... TEST NO ~SYMBO~
N
1 C)
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~
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N
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0
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-------
o
C?
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o
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0
1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
GTCP85-115 SIN P-18781 O/H. FUEL AV.KEROS. DATE 6/8/71 CELL 0-111
GT-8747-R
AppeT1dix D .
-------
o
C?
N TEST NO.SYMBOL
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1.00
2.00
3.00
I
4.00
I I
5.00 6.00
PROBE NO.
I
7.00
I
8.00
I
9.00
~
10.00
GTCP85-115 SIN P-18781 O/H. FUEL RV.KEROS. oRTE 6/8/71 CELL 0-111
GT-8747-R
Appendix D
-------
o
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lJ) TEST NOaSYMBOL
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1.00
2.00
I
3.00
I
4.00
I I
5.00 6.00
PROBE NO.
I
7.00
I
8.00
I
9.00
---,
10.00
GTCP85-115 SIN P-18702. O/H. FUEL JP4 ORTE 6/11/71 CELL 0-111
GT-8747-R
Appendix D
-------
o
~
0
CD TEST NO.SYMBOL
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PROBE NO.
GTCP85-115 SIN P-18702. O/H. FUEL JP4 DATE 6/11/71 CELL 0-111
GT-8747-R
Appendix D
-------
o
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I
7.00
I
8.00
I
9.00
-',
10.00
GTCP85-115 SIN P-18702. O/H. FUEL JP4 ORTE 6/11/71 CELL 0-111
GT-8747-R
Appendix D.
-------
o
C?
<0 TEST NO.SYMBOL
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
GTCP85-115 SIN P-18702. O/H. FUEL JP4 DATE 6/11/71 CELL 0-111
GT-B747-R
Appendix D
-------
o
~
lJ) TEST NO.SYMBOL
c-
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1.00 2.00 3.00 4.00 5.00 10.00
PROBE NO.
GTCP85-115 SIN P-18702. O/H. FUEL JP4 oRTE 6/11/71 CEllO-ill
GT-8747-R
Appendix D
-------
o
~
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2.00
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3.00
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4.00
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5.00 6.00
PROBE NO.
I
7.00
I
8.00
I
9.00
--,
10.00
GTCP85-129 SIN P-34763, O/H, FUEL JP4, DRTE 4/28/71
GT-8747-R
Appendix D
Page 121
-------
o
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5.00 6.00
PROBE NO.
I
7.00
I
8.00
I
9.00
---,
10.00
GTCP8S-129 SIN P-34763. O/H. FUEL JP4. DATE 4/28/71
GT-8747-R
Appendix D
Page 122
-------
o
C?
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-------
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C!
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PROBE NO.
GTCF85-129 SIN P-34763. O/H. FUEL JP4. DRTE 4/28/71 CELL C-102
GT-8747-R
Appendix D
-------
C>
C?
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PROBE NO.
GTCP85-129 SIN P-34763. O/H. FUEL JP4. DATE 4/28/71 CELL [-102
GT-B747-R
Appendix D
-------
o
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U) TEST NO.SYMBOL
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15.00 16.00
PROBE NO.
FUEL JP5. DATE 5/18/71.
GT-8747-R
. Appendix D
Page 126
I
7.00
17.00
I
8.00
18.00
I
9.00
19.00
---,
10.00
20.00
GTC85-90. SIN P-5786. O/H.
-------
a
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PRO BE NOs
GTC85-90. SIN P-5786. O/H. FUEL JP5. DATE 5/18/71. CELL NO.D-111
)( GT-8747-R
A~pendix D
-------
o
c:
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L/) Z Z
~ ~ ~ ~ y i ~ ~
o ~ ~ ~
c:
0 I I I I I I I I I
1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
11. 00 12.00 13 .00 14.00 15.00 16.00 17.00 18.00 19.00 20.00
PRO BE NO.
GTC85-90, SIN P-5786, O/H, FUEL JP5, DATE 5/18/71, CELL NO.D-111
GT-8747-R
Appendix D
-------
o
C?
N TEST NO.SYMBOL
Ln
1 C)
0 2 6
0 PC PROBE
)!( 5 )!( ~
C? )!(
... 1 4-
...
)!( 2 x:
3 Z PROBE
0 LOCATION
C? Y Y 4 Y 11-20
0
. y 5 ~
)!(
0 y y y
C?
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y
0
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N X
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0 Z X
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0
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Q:)N X Z
~ Z
CL.. Z
CL..
0
'0 z
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+ +
o +
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C?
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1.00 2.00 3.00 4.00 5.00 ~O ~O ~ 10.00
(!) (!) &ROBE N .
11. 00 12.00 13.00 14.00 15.00 16.00 17.00 18.00 19.00 20.00
GTC85-90. SIN P-5786. O/H. FUEL JP5. DATE 5/18/71. CELL NO.D-l11
GT-8747-R
Appendix D
-------
o
C!
0 TEST NO.SYMBOL
to
1 C)
0 2 6
C! PROBE
to 3 + LOCATION
LJ)
1-10
4 X
0 )!{ ~ ~ 5 ~
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(,'oJ )!{ 1 ~ ~
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3 Z LOCATION
0 11-20
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to
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x x x x
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to
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x: x: x: L!> L!> L!> x:
x: x: 1f\
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C! L!>
.,. x:
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o
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C9 C9 C9 C9 C9
o
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
11. 00 12.00 13.00 14.00 15.00 16.00 17.00 18.00 19.00 20.00
PROBE NO.
GTC85-90. SIN P-5786. O/H. FUEL JPS. DATE 5/18/71. CELL NO.D-111
GT-8747-R
Appendix D
-------
o
IX:!
v TEST NO. SYMBOL-
1 (2)
0 2 6
"'!
v 3 +
4 X
0 5
~
v
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(T)
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ro
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u X
a::: X
w
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a + +
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0 C9 C9 C9 C9 C9 C9 C9
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o
ro
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a
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1.00
I
7.00
I
8.00
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10.00
2.00
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4.00
5.00 6.00
FROBE NO.
GTC85-90-2 SIN P-24504. PROD. FUEL JP4 DATE 5/5/71. CELL 884
GT-8747-R
Appendix D
-------
o
c:;>
0
0
2 ~
0
.U1 3
U1 +
x x 4 X
x
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5.00 6.00
PROBE NO.
I
7.00
I
8.00
I
9.00
---,
10.00
GTC85-90-2 SIN P-24504. PROD. FUEL JP4 DRTE 5/5/71. CELL 884
GT-8747-R
Appendix D
-------
o
~
v TEST NOoSYMBOL
N
1 C)
g 2 ~
N 3
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C) 4 X
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+
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v
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
GTC85-90-2 SIN P-24504. PROD. FUEL JP4 DRTE 5/5/71. CELL 884
GT-8'74 7-R
Appendix D
-------
o
C!
CD
.... TEST NO. SYMBOL
1 C)
0 2 L!:,.
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4 X
0 5 0
C!
0
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o
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o 6 ~ 6
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0
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
GTC85-90-2 SIN P-24504. PROD. FUEL JP4 DRTE 5/5/71. CELL 884
GT-8747-R
Appendix D
-------
o
C?
tD TEST NO.SYMBOL
Ln
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Ln
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o
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o
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1.00
I
2.00
I
3.00
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4.00
, ,
5.00 6.00
PROBE NO.
I
7.00
I
8.00
I
9.00
---,
10.00
GTC85-90-2 SIN P-24504. PROD. FUEL JP4 DRTE 5/5/71. CELL 884
GT-8747-R
Appendix D
-------
o
~
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1 C)
0 2 A
"! PROBE
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1-10
4 X
0 5 0
C? 1 ~
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o
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1.00
11. 00
O/H
5.00 6.00
15.00 16.00
PROBE NO.
FUEL JP-S
GT-8747-R
Appendix D
Page 136
7.00
17.00
8.00
18.00
.
9.00
19.00
I
10.00
20.00
2.00
12.00
3.00
13 .00
4.00
14.00
GTC8S-90-B SIN P-24376
DRTE 6/16/71 PROBES 1-20
-------
o
o
o
o
UJ
o
o
o
In
In
o
o
o
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1-10
4 X
;l z 5 z ~ ~
Z + 1 + ~
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J;: ~ ~ 3 Z LOCATION
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~ 4 x Y 6
X X
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10.00
20.00
2.00
12.00
3.00
13 .00
4.00
14.00
5.00 6.00
15.00 16.00
PROBE NO.
FUEL JP-5
GT-8747-R
Appendix D
Page 137
7.00
17.00
8.00
18.-00
9.00
19.00
GTC85-90-B SIN P-24376
O/H
-------
o
u:.!
en TEST NO.SYMBOL
1 (')
0 2 ~ PROBE
~
-------
o
C!
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~
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1-10
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5.00 6.00
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PRO BE NO.
FUEL JP-5
GT-8747-R
Appendix D
Page 139
.
7.00
17.00
I
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18.00
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9.00
19.00
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10.00
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GTC85-90-B SIN P-243760/H
-------
o
C?
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A DIVISION 0" TH~ GARRETT CDRPQRATION
GROUP 4
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POWER UNITS
-------
°
IX?
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PROBE NO.
GTCP660-4
SIN P-37596 O/H FUEL JP5
DRTE 5/26/71
CELL 72
GT-8747-R
Appendix D
-------
o
c::
0
tD TEST NO. SYMBOL
N
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PROBE NO.
GTCP660-4 SIN P-37596 O/H FUEL JP5 DRTE 5/26/71 CELL 72
GT-8747-R
Appendix D
-------
o
~
c- TEST NO. SYMBOL
1 (l)
o 20 ~
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-------
o
c:
lD TEST NO. SYMBOL
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0
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PROBE NO.
GTCP660-4 SIN P-37596 O/H FUEL JP5 DRTE 5/26/71 CELL 72
GT-8747-R
Appendix D
-------
o
C?
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PROBE NO.
GTCP660-4 SIN P-37596 O/H FUEL JP5 DRTE 5/26/71 CELL 72
GT-8747-R
Appendix D
-------
a
a:
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I
7.00
,
8.00
I
9.00
I
10.00
GTCP660-4
SIN P-37705
PROD. FUEL JP5 DATE 5/25/71
GT-8747-R
Appendix D
Page 146
-------
o
~
0
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N
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PROBE NO.
GTCP660-4 SIN P-37705 PROD. FUEL JP5 DRTE 5/25/71 CELL 72
GT-8747-R
Appendix D
-------
o
C?
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I
7.00
I
8.00
I
9.00
I
10.00
GTCP660-4
SIN P-37705
PROD. FUEL JP5 DATE 5/25/71
GT-8747-R
Appendix D
Page 148
-------
o
c:
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PROBE NO.
GTCP660-4 . SIN P-37705 PROD. FUEL JP5 DRTE 5/25/71 CELL 72
GT-8747-R
Appendix D
-------
a
~
U) TEST NO. SYMBOL
c-
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PROBE NO. C9
GTCP660-4 SIN P-37705 PROD. FUEL JP5 DRTE 5/25/71 CELL 72
GT-8747-R
Appendix D
-------
o
U)
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C)
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PROBE NO.
TSCP700-4 SIN P-90122 PROD. FUEL JP5 DRTE 5/25171 CELL 75
GT-8747-R
Appendix D
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PROBE NO.
TSCP700-4 SIN P-90122 PROD. FUEL JP5 DRTE 5/25/71 CELL 75
GT-8747-R
Appendix D
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I
7.00
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9.00
I
10.00
TSCP700-4
SIN P-90123
DRTE 5-27-71
JP5 FUEL
CELL 75
DP2=STRNDBY ID
GT-8747-R
Appendix D
-------
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1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
PROBE NO.
TSCP700-4 SIN P-90123 DRTE 5-27-71 JP5 FUEL CELL 75 DP2=STRNDBY 10
GT-8747-R
Appendix D
-------
-------
~
AIRESEARCH MANUF"ACTURING COMPANY OF" ARIZONA
A DIVISIDN OF' THE GARRETT CORPORATION
APPENDIX E
FUEL ANALYSIS
TYPICAL GAS SAMPLING ANALYZER TRACES
GT-8747-R
-------
Specification
Grade
Fuel Type
Gravity, °API (Sp. Gr.)
Distillation, of
Initial Boiling Point
5 Percent Evaporated
10 Percent Evaporated
20 Percent Evaporated
30 Percent Evaporated
40 Percent Evaporated
50 Percent Evaporated
60 Percent Evaporated
70 Percent Evaporated
80 Percent Evaporated
90 Percent Evaporated
95 Percent Evaporated
Final Boiling Point
Distillation Loss, Percent
Flash Point, of
Reid Vapor Pressure, psi
Viscosity at 100°F, cSt
at -30°F, cSt
Aromatics, Vol Percent
Olefins, Vol Percent
Smoke Point, mm
Smoke Volatility Index
Heat of Combustion, Net Btu!lb
Hydrogen - Carbon Weight Ratio
~:
PROPERTIES OF TEST FUELS
USED IN OAP/EPA EXHAUST EMISSION STUDY
Aviation Turbine Fuels
Diesel Fuel
MIL-T-5624G
MIL-T-5624G
ASTM D 1655-68
W-F-800
JP-4
JP-5
Jet A
DF-2
Wide Cut
Kerosene
Kerosene
Regular Diesel
49.9 (0.780)
39.8 (0.826)
43.1 (0.810)
34.6 (0.852)
180
228
240
260
276
292
312
328
340
366
392
413
448
98.5
352
372
380
385
398
404
410
418
426
437
454
469
486
98
324
352
362
377
388
398
408
419
431
446
466
484
499
98
156 (2 )
396
431
445
464
482
498
514
532
552
572
605
651
94
160
196
1.20(1)
1. 59
1.49
2.94
7
12
16
10
49
15
29
1
2
1
24 (3)
2
26
22
16
64.6
18,520
O. 1671
18 , 43 0
18,470
18,280
0.1576
O. 1618
0.1507
(1)
(2 )
Reid Vapor Pressure of JP-4 does not meet MIL-T-5624G specification of 2.0-3.0 psi.
Flash Point of Jet A does not meet ASTM D 1655-68 specification of 110-150°F.
(3 )
Smoke Point of Jet A does not meet ASTM D 1655-68 specification of 25 min minimum.
GT-8747-R
Appendix E
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