AR-816
GASEOUS EMISSIONS FROM A LIMITED
SAMPLE OF MILITARY AND COMMERCIAL
AIRCRAFT TURBINE ENGINES
by
Charles T. Hare
Harry E. Dietzmann
Karl J. Springer
INTERIM REPORT
Contract No. EHS 70-108
for
Division of Emission Control Technology
Air Pollution Control Office
Environmental Protection Agency
August 31, 1971
SOUTHWEST RESEARCH INSTITUTE
SAN ANTONIO
HOUSTON
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SOUTHWEST RESEARCH INSTITUTE
Post Office Drawer 28510, 8500 Culebra Road
San Antonio, Texas 78284
Vehicle Emissions Research Laboratory
GASEOUS EMISSIONS FROM A LIMITED
SAMPLE OF MILITARY AND COMMERCIAL
AIRCRAFT TURBINE ENGINES
by
Charles T. Hare
Harry E. Dietzmann
Karl J. Springer
INTERIM REPORT
Contract No. EHS 70-108
for
Division of Emission Control Technology
Air Pollution Control Office
Environmental Protection Agency
August 31, 1971
Approved
>hn M. Clark, Jr., Director
Department of Automotive Research
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FOREWORD AND CREDITS
The work described and documented in this report was performed
under contract number EHS 70-108, and constituted an expansion of Task II
(Laboratory Emissions Measurements) of the original Scope of Work, effec-
tive June 14, 1971. The agency for which the subject work was performed
is the Division of Emission Control Technology, Air Pollution Control Office,
Environmental Protection Agency, 5 Research Drive, Ann Arbor, Michigan,
48103. The Project Officer was Mr. B. D. McNutt, and the Contract
Administrator was Mr. William Ciller. This interim report and the research
program on which it is based fulfill partially the requirements of the contractor,
the Vehicle Emissions Research Laboratory of Southwest Research Institute,
8500 Culebra Road, San Antonio, Texas, 78284. Overall supervisor of the
subject program was Karl J. Springer, program coordination, data analysis,
and reporting were done by Charles T. Hare, and Harry E. Dietzmann super-
vised data acquisition and the field crew. The crew members were Ernest W.
Dietzmann, Russel T. Mack, Del Ray O'Neill, and Patrick K. Allen.
Acquisition of baseline aircraft turbine emissions data from a large
number of engines in a limited amount of time required the cooperation of
a number of people at Kelly AFB, San Antonio, and at the Trans World
Airlines Overhaul Facility in Kansas City, Missouri. Although it is impos-
sible to acknowledge all those whose cooperation was valued, the following
lists include at least some of those who worked with the contractor to
achieve program goals.
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Cooperating personnel at Kelly AFB; Mr. A. E. Wright, Captain
J. F. Sharp, Messrs. Kellerman, Herndon, Zedler, Bachmann, and
George Miller, plus the test cell crews.
Cooperating personnel at TWA; Messrs. Tom King, Dave Hartline,
Clark A. Fisher, John Works, Carl Ferrara, George Kolias, Larry
Thompson, Jack Metcalf, Don Hutchison, Olie Oldehoft, and Fred Coleman,
plus others in the test operation.
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ABSTRACT
The objective of the aircraft turbine emissions measurement phase
of this program was to provide the sponsor with baseline gaseous emissions
data, including hydrocarbons, carbon monoxide, carbon dioxide, and oxides
of nitrogen, in a very limited time frame. Seventy-one tests were conducted
in all, first on two types of military engines at Kelly AFB in San Antonio and
later on six types of commercial engines at the Trans World Airlines overhaul
facility in Kansas City, Missouri. The work is documented, data are
presented, and brief summaries and analyses are given.
IV
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TABLE OF CONTENTS
Page
FOREWORD AND CREDITS ii
ABSTRACT iv
LIST OF ILLUSTRATIONS vi
LIST OF TABLES viii
I. INTRODUCTION 1
II. PROJECT COORDINATION 2
III. PREPARATIONS AND INSTRUMENTATION 8
IV. OPERATIONS AT KELLY AFB, SAN ANTONIO 12
V. OPERATIONS AT TWA OVERHAUL FACILITY,
KANSAS CITY 17
VI. BRIEF DATA SUMMARY AND ANALYSIS 20
A. T-56 Turboprop Engines, Kelly AFB 20
B. J-79 Turbojet Engines, Kelly AFB 22
C. Commercial Turbojet and Turbofan
Engines, TWA, Kansas City 23
D. Effects of a Commercial Smoke-Suppressant
Fuel Additive and Emission Maps for Four
Types of Commercial Engines 33
VII. SUMMARY AND COMMENTS 43
APPENDIXES
A. Data on Emissions from T-56 Turboprop Engines
B. Data, on Emissions from J-79 Turbojet Engines
C. Data on Emissions from Commercial Turbojet and
Turbofan Engines: JT3C-6, JT3D-3B, JT4A-11,
JT8D-1, JT8D-7, JT8D-9, and CJ-805
D. Fuel Specifications
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LIST OF ILLUSTRATIONS
Figure Page
1 Original Design of Aircraft Gas Turbine Sampling Probe 6
2 Second Design of Aircraft Sampling Probe 6
3 Third Design of Aircraft Sampling Probe 6
4 Fourth Design of Aircraft Sampling Probe 6
5 Aircraft Emissions Analysis Cart On Site, Front View 10
6 Aircraft Emissions Analysis Cart Under Construction,
Rear View 10
7 Hydrocarbon Analyzer Detector/Oven Assembly
and Acoustic Enclosure 10
8 Sample Driers and Filters in Test Cell 10
9 View of Probe and Mount Behind Engine from
Entrance to Test Cell 56, Kelly AFB 14
10 View of Hydrocarbon Analyzer Detector Installation
in Test Cell 56, Kelly AFB 14
11 View Up Stairs Toward Exit from Test Cell 56,
Kelly AFB 14
12 Detail of Probe and Mount Used for T-56 Engines,
Test Cell 56, Kelly AFB 14
13 Installation of Hydrocarbon Detector and Rear
Entrance, Test Cell 48, Kelly AFB 15
14 J-79 Engine and Exhaust Bellmouth in Test Cell 48,
Kelly AFB 15
15 Original Probe Mount in Place in Test Cell 48,
Kelly AFB 15
16 Modified Probe Mount in Place in Test Cell 48,
Kelly AFB 15
17 Test Cell 5, TWA Overhaul Facility, Kansas City 18
VI
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LIST OF ILLUSTRATIONS (Con't)
Figure Page
18 Exhaust Bellmouth and Support Rails, Test Cell 5,
TWA Overhaul Facility, Kansas City 18
19 Detector Assembly of Hydrocarbon Analyzer
Installed in Pump Room for TWA Testing 18
20 Analysis and Output Instruments Installed in
Control Room for TWA Testing 18
21 Filters Used During Tests on a JT8D-9 Engine 36
22 Filters Used During Tests on a JT4A-11 Engine 36
23 Filters Used During Tests on a CJ-805 Engine 36
24 Filters Used During Tests on a JT3D-3B Engine 37
25 Filters Used During Tests on a JT8D-1 Engine 37
26 Gaseous Emissions Map for a JT8D-1 Turbofan
Engine (Test 65) 38
27 Gaseous Emissions Map for an In-Service JT8D-9
Turbofan Engine (Test 68) 39
28 Gaseous Emissions Map for a New JT8D-9 Turbo-
fan "Calibration" Engine (Test 69) 40
29 Gaseous Emissions Map for a JT4A-11 Turbojet
Engine (Test 70) 41
30 Gaseous Emissions Map for a JT3D-3B Turbofan
Engine (Test 71) 42
Vll
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LIST OF TABLES
Table Page
1 Results of Naming EPA Gas Cylinders, 6/17/71 4
2 Data on Gaseous Emissions from T-56 Turboprop
Military Engines 21
3 Data on Gaseous Emissions from J-79 Turbojet
Military Engines 22
4 Data on Gaseous Emissions from JT8D-9
Commercial Turbofan Engines 24
5 Data on Gaseous Emissions from JT8D-1
and JT8D-7 Commercial Turbofan Engines 25
6 Data on Gaseous Emissions from JT4A-11
Commercial Turbojet Engines 27
7 Data on Gaseous Emissions from JT3D-3B
Commercial Turbofan Engines 29
8 Data on Gaseous Emissions from JT3C-6
Commercial Turbojet Engines 30
9 Data on Gaseous Emissions from CJ-805
Commercial Turbojet Engines 31
10 Comparison of Baseline Gaseous Emission from Six
Type.s of Commercial Engines in Four Common Modes 32
11 Comparison of Gaseous Emissions Using Untreated
and Additive-Treated Fuels 34
Vlll
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I. INTRODUCTION
Recent amendments to the Clean Air Act have emphasized the
importance of Federal emission standards which are soon to be set on
aircraft turbine engines. Data required as basis for these standards
were not available, so several groups were directed or placed under con-
tract to gather data on-site at military and commercial installations
beginning during the spring of 1971. As a participant in the data acquisi-
tion effort, the SwRI Vehicle Emissions Research Laboratory conducted
tests at Kelly AFB and at the TWA overhaul facility in Kansas City. All
the tests were restricted to measurement of gaseous emissions, namely
hydrocarbons, CO, CO£, and oxides of nitrogen. A qualitative appraisal
of the effects of a commercial smoke-suppressant fuel additive was obtained
by recovering sample line filters used at TWA during tests using untreated
fuel and treated fuels containing two different concentrations of the additive.
Data have been submitted as obtained on the uniform baseline data sheets,
and these data will be summarized and given as Appendixes.
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II. PROJECT COORDINATION
In response to Request for Proposal EPAR 70-Neg. 142, dated
April 1, 1971, the SwRI Vehicle Emissions Research Laboratory submitted
a proposal, no. 11-7916, "Aircraft Gas Turbine Engine Emission Testing."
This document, dated April 14, 1971, proposed a modification to the
existing contract EHS 70-108, "Study of Exhaust Emissions from Uncon-
trolled Vehicles and Related Equipment Using Internal Combustion Engines. "
The modification became effective June 14, 1971, by which time the work
efforts had been in progress for about a month.
Chronologically, the initial coordination of this program began by
telephone in March of 1971, and agreement on the scope of work was
essentially completed during the Project Officer's visit to the Institute
on April 16, 1971. The informal plan of attack was to begin preparations
about mid-May, start sampling at Kelly AFB on June 15, switch to TWA
in Kansas City about July 12, and wind up the sampling operation on
August 13. This schedule was adhered to throughout, and the Interim
Report on the aircraft turbine emissions measurements (the subject report)
was due August 31. 1971. During the Project Officer's visit to SwRI, a
short tour of the test cell area at Kelly AFB was conducted by Captain
J. F. Sharp to familiarize both sponsor and contractor with the facilities.
This visit and one later visit by contractor's representatives prior to the
onset of emissions measurements were adequate for planning and setting
up instrumentation. The systems used were necessarily designed to be
flexible due to the structural differences in the test cells to be used, and
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the instrumentation systems had to be "ruggedized" for transit and to
operate in environmental extremes.
The next major coordination effort was a visit to the TWA Overhaul
Facility in Kansas City, Missouri, by the Project Officer and a contractor's
representative on June 3, 1971. This visit and another one by the contractor's
representative alone later in June provided enough communication to arrange
the TWA tests well in advance. Later in the day on June 3, a meeting was
held in Tulsa with representatives of EPA, SwRI, Bureau of Mines-Bartles-
ville, and Scott Research Lab present. The agenda for this meeting included
discussions on probe design and sampling systems, format for uniform data
sheets, a briefing on allocation of tasks for the entire aircraft emissions
measurement program, and a briefing on an EPA sampling system cor-
relation effort to be conducted by Mr. Gordon Becker under the supervision
of Mr. Merrill Korth. The first model of the aircraft turbine sampling probe
(serial no. 1) was carried to the Tulsa meeting and delivered to Mr. Jim
Chase at the meeting's close for use in the Bureau of Mines-American
Airlines effort.
The "naming" of EPA gas cylinders by the several groups involved
in the aircraft sampling work was the method of correlation chosen by the
sponsor. In the case of SwRI, this procedure involved escorting Mr. Gordon
Becker to Test Cell 56 at Kelly AFB and naming the gases he carried as
time permitted between runs on T-56 engines. The calibration gases used
by SwRI on a routine basis are those which have previously been named by
EPA or are directly traceable to EPA-named gases, so it was expected
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that the SwRI naming would be close to that of EPA. Two problems were
encountered, however, which may have had some influence on the results.
First, the named gases held by SwRI at the onset of the aircraft program
were generally in concentration ranges much higher than those in which the
aircraft instruments were calibrated. Second, difficulty was encountered
in obtaining low-concentration calibration gases for this project in a
reasonable length of time, forcing the use of calibration curves constructed
from fewer points than the number considered desirable. Table 1 presents
the concentrations named by SwRI and those named by EPA as given the
test crew following the calibration.
TABLE 1. RESULTS OF NAMING EPA GAS CYLINDERS, 6/17/71
Cylinder No.
Gas
EPA Concentration
SwRI Concentration
A-42334
SSB-162
A-6741
A-672
A-6775
A-247
SG-13359B
NO
NO
C02
C02
CO
HC
HC
82. 2 ppm NOX
21. 0 ppm NOX
4. 22% C02
1. 57% C02
82 ppm CO
72. 2 ppm C3
10. 5 ppm C3
82. 0 ppm NOX
19. 0 ppm NOX
4.05% CO2
1.53% C02
94 ppm CO
67. 5 ppm C^
8. 4 ppm C3
AIR
0.1 ppmC
ppm
One of the most important phases of program coordination involved
the design, production, and distribution of exhaust sampling probes. The
production and distribution functions were undertaken by SwRI at the sponsor's
request to provide identical probes to all the measurement teams. The basic
design, allegedly derived from a similar Pratt & Whitney probe, was a
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lightly-qualified disaster. It was not a complete disaster only because
enough probes held together long enough so that some data could be col-
lected, but a prerequisite to any further work in aircraft turbine sampling
must surely be the design of an adequate probe.
The probe used for this study was based somewhat on stationary-
source stack sampling procedures, in that the holes through which the
sample entered were spaced out from the probe centerline at the area
centers of three equal areas. Figure 1 shows a typical probe of the initial
design, made of 316 stainless steel, as were all subsequent models. The
formula used to calculate the hole radii for circular ducts was
Rn = d/(2n-f)74N, where
Rn = radius of nth point from center of duct, inches
d = diameter of duct, inches
N = number of points to be spaced across diameter of duct.
= 6 (for the aircraft work)
When N=6, as was the case for all the aircraft probes, 1/6 of the total
duct area fell inside RI , half the total area inside R2, and 5/6 of the total
area inside R3. In other words, Ri=0.204d, R2 = 0. 354d, andR3-0.456d
when N=6 for a circular duct. Most of the probes made by SwRI were for
engines having circular tailpipes, but four types of engines being tested
(JT3C-6 and -7, JT4A-3, JT4A-11, and CJ-805) were equipped with silencers.
These silencers were of several configurations, but all had 8 lobes, and all
were symmetrical except the JT4A-3 design. The procedure followed on
these engines was to obtain or construct a layout of the exhaust nozzle and
analyze 1/8 of the layout (45°) geometrically by breaking it up into familiar
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Figure 1. Original Design of
Aircraft Gas Turbine Sampling
Probe
Figure 2. Second Design of
Aircraft Sampling Probe
Figure 3. Third Design of
Aircraft Sampling Probe
Figure 4. Fourth Design of
Aircraft Sampling Probe
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shapes (circles, sectors, annuli, trapezoids, ellipses, etc. ). Based on
this analysis, the total area of one lobe was calculated, and it was not
difficult at that point to find the radii inside which 1/6, 1/2, and 5/6 of the
total area lay. This analysis was not sufficient for the asymmetrical
JT4A-3 design, so a polar planimeter was used to find the total area, then
used again on a trial-and-error basis to locate the sampling hole radii.
As sampling probes failed in the field, modifications were made in
the basic structure to give the probes additional strength. Figure 2 shows
a probe made on the second basic design, with thicker-wall tubing in the
radial elements (0. 065 inch wall as compared to 0. 049 wall in the earlier
model) and 1/8 inch-thick triangular gussets extending out 5 inches from the
center body. The second design also incorporated a smaller bore through
the center body to accommodate a 1/4 NPT female thread at the rear, and the
threaded hole at the side of the probe toward the rear was made optional.
The third probe design is shown in Figure 3, the full-length 1/8 inch-thick
gussets being the only change from design 2. Figure 4 shows the last design
tried, with 2 inch-wide, 1/4 inch-thick gussets straight out to 2/3 the arm
length and then tapered to the tips. These gussets were also tapered along
the trailing edge to simulate a crude airfoil, and the ring welded at the 2/3
arm length radius was included to help prevent flap-mode vibrations. The
center body was lengthened 1 inch for this design to keep the body length
available for gripping about constant. In all, 26 probes were constructed
and shipped between June 3 and July 23; twelve for use by SwRI, four for
the EPA/United Air Lines operation, six for the Bureau of Mines/American
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Airlines effort, and four for the Scott/Norfolk Naval Air Station tests.
III. PREPARATIONS AND INSTRUMENTATION
As noted previously, the urgency of the aircraft turbine emissions
program brought the remainder of the off-road emission sources project to
a temporary halt. This measure was necessary in order to obtain the
services of the most highly-skilled personnel available at all levels, and was
a consequence accepted by the Sponsor. Preparations for the aircraft
sampling work began about May 20, 1971, and involved a considerable
amount of instrumentation and sampling train buildup, data form design,
and coordination with supervisory personnel at Kelly AFB and TWA - Kansas
City. The instrumentation required for low emission levels was the most
difficult problem. A new hydrocarbon analyzer and control system was
fabricated from scratch, including a fan-cooled chamber which acoustically
isolated the detector/oven assembly from the ambient to allow operation of
the detector in the engine test cells. This unit included the best control
systems available to assure stable operation, including a remote input head
for the electrometer, solid-state oven and line heater controls, and remotely
controlled calibration. This instrument gave excellent results, with
resolution better than 1 ppmC on its most sensitive range and the capability of
accurate measurements to several thousand ppmC. The short sample line
permitted by the in-cell location of the detector provided excellent response.
A few problems arose regarding delivery of a chemiluminescent
NO-NOX analyzer by Thermo Electron Corporation, but as things turned out,
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two TECO analyzers were finally incorporated into the system for the
Kelly AFB operation. These instruments generally performed very well,
although they suffered a few vacuum pump problems which have since been
rectified by the manufacturer's specification of a higher-quality pump.
Only one of these analyzers, the one furnished by EPA for the subject work,
was used in Kansas City. The lead time on the aircraft work was not suf-
ficient to permit acquisition of a long-path NDIR CO instrument (normal
availability 90 to 120 days), so a new Beckman model 3 ISA low-range
instrument which had been reserved for diesel emissions tests was modified
by installing a longer cell and subsequently used for the turbine sampling.
This instrument worked quite well, providing a wide enough range of
sensitivity for the engines tested. The instrument used for CO£ measure-
ment was a Beckman model 315, and it proved satisfactory, although a
newer unit would have been desirable.
Figure 5 is an overall photograph of the aircraft emission analysis/
output unit. At top left are the output modules of the two NOX analyzers,
and the analysis sections of these two instruments are at bottom left. The
amplifier sections of the two NDIR instruments are shown under the NOX
output modules, and the NDIR analyzer sections are at bottom center. The
strip chart recorder at right is a 4-channel unit with overlapping pens and
fast-response servomotors. Figure 5 also shows the control panel and
electrometer for the hydrocarbon analyzer (top right of cart), and the panel
at bottom right contains switches, pilot lights, flow-switching and restricting
valves, a sample pressure gauge, and two (unused) dessicant canisters.
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Figure 5. Aircraft Emissions
Analysis Cart On Site
Front View
Figure 6. Aircraft Emissions
Analysis Cart Under
Construction, Rear View
Figure 7. Hydrocarbon
Analyzer Detector/Oven
Assembly and Acoustic
Enclosure
Figure 8. Sample Driers and
Filters in Test Cell
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Figure 6 shows the rear of the analysis system, with sample pumps
(bottom left) and vacuum pumps for the NOX analyzers (bottom right)
mounted outboard to reduce vibration in the sampling train. The two
modules strapped together at the lower right corner of the cart are NO2
converters for the chemiluminescent NOX analyzers, and the black box at
the lower left corner is one of the two power supplies for the NDIR analyzers.
Figure 7 shows the box which housed the hydrocarbon analyzer's
detector/oven/pump assembly. The box is double-walled and insulated to
prevent mechanical or acoustic noise from affecting the oven inside. The
unit only partially in view at the extreme right of the cart is the remote
input head for the electrometer, and the gas cylinders on the two lower
shelves contained fuel, air, and calibration gases. Figure 8 shows the
sample driers which were in the sample line downstream of the point where
the hydrocarbon analyzer's sample was taken. These driers were used to
avoid the use of a sample line heated all the way to the other analyzers (up
to 50 ft) which would be different for each test cell. If sampling operations
were to be done in a single location, a long, heated line would be the recom-
mended procedure, but the increased set-up time could not be tolerated
during this time-critical project where mobility was a necessity. Tests
were conducted on the sampling train used for this project, and it was found
that instrument readings on calibration gases entering at the probe mount
were the same as those entering at the calibration gas inlet (near the
instruments) within 1%. These tests were conducted with both NO2 and CC>2
calibrating gases and with the system in both clean and dirty conditions.
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The remaining preparations for the aircraft sampling work at Kelly
AFB were primarily in the area of obtaining clearances and coordinating
with several levels of military and civil service personnel. In due course,
the required permits were obtained, although permission to photograph
the sampling equipment in place was not easy to come by. The entire
operation at Kelly, as well as that at TWA, went off very smoothly, in part
due to careful coordination with personnel and sincere attempts to interfere
with normal operations as little as possible.
IV. OPERATIONS AT KELLY AFB, SAN ANTONIO
Following the schedule set forth earlier, equipment installation and
setup were begun in Test Cell 56 at Kelly AFB on June 15, 1971. On-site
preparations consumed slightly more time than had been expected, and the
first successful test on a T-56 engine was carried out on June 17. The
major complication experienced with setting up for operation in Cell 56
was that the control room and area for placement of instruments were more
than one story (approximately 25 feet) above ground level. This construction
is peculiar to test cells for engines which drive propellers, and is necessary
to achieve clearance for the propeller swing, but it made necessary the
disassembly of most of the larger equipment items and their subsequent
reassembly after having been carried up two flights of stairs.
Photographs presented earlier in the report, Figures 5. 7, and 8,
show equipment in place at Cell 56. Figure 5 was taken in the access area
outside the cell, and Figures 7 and 8 were shot inside the cell. The floor
of the access area and the control room were about 6 feet above the engine
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platform where the probe was mounted, and Figures 9, 10, and 11 document
this relationship. Figure 9 was taken from the landing just inside the test
cell from the door leading out to the access area, and was shot downward
to show the probe, the mount, and an engine tailpipe. Figure 10 shows again
the hydrocarbon analyzer's detector unit enclosed in its acoustic chamber
under the stairs. The heated section of the sample line is shown at right,
and the engine tailpipe and probe are visible (out of focus) at lower left.
Figure 11 was shot directly toward the stairs leading upward out of the
cell, and also shows the sample line/control cable bundle twisting its
way toward the hole through the blast wall where it entered the access area.
Figure 12 is a more detailed view of the probe and probe mount in place
behind an engine. The thrust stand was constructed so that engines had
to be slipped into it from the rear, so it was necessary to dismount the
probe while engines were being removed or installed. As of June 24,
thirteen T-56 engines had been tested, and it was decided to move the
equipment to Test Cell 48, where J-79 turbojets underwent acceptance
testing.
The physical arrangement of cell 48 made it much less difficult to
work in than cell 56. To avoid vertical movement, the remote analysis
equipment (shown previously in Figure 5) was installed in the pump room
to the rear of the test cell. Access to the pump room was provided by the
short stairway and door shown in the background at left in Figure 13. This
photograph, taken before equipment installation was complete, also shows
the position of the hydrocarbon analyzer's detector relative to the exhaust
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Figure 9. View of Probe and
Mount Behind Engine from
Entrance to Test Cell 56,
Kelly AFB
Figure 10. View of Hydrocarbon
Analyzer Detector Installation
in Test Cell 56, Kelly AFB
Figure 11. View up Stairs
Toward Exit from Test Cell 56,
Kelly AFB
Figure 12. Detail of Probe and
Mount Used for T-56 Engines,
Test Cell 56, Kelly AFB
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Figure 13. Installation of Hydro-
carbon Detector and Rear Entrance,
Test Cell 48, Kelly AFB
Figure 14. J-79 Engine and
Exhaust Bellmouth in Test
Cell 48, Kelly AFB
Figure 15. Original Probe Mount
in Place in Test Cell 48, Kelly AFB
Figure 16. Modified Probe Mount
in Place in Test Cell 48, Kelly AFB
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bellmouth and the arrangement by which the probe mount was fastened to
the bellmouth support rail. Figure 14 shows a J-79 engine in position
before the sampling equipment was installed. This engine is equipped
with an afterburner and a fully variable exhaust nozzle, which made it
necessary to design and fabricate a probe mount which could be retracted
out of the exhaust flow when the afterburner was in operation. Figure 15
shows the mount in its original configuration, hinged at the junction of arm
and base and operated by a double-acting air cylinder. The arm's move-
ments were dictated by electric servo valves which were switch-actuated
by a technician located in a protected viewing area just aft of the exhaust
nozzle. The original probe mount design was not rigid enough, so the
modification shown in Figure 16 was made following the first test with the
original mount. The truss added to stiffen the mount reduced the vibration
encountered with the original design, and the jacks under the mount provided
a pre-load which served to dampen movement to an even greater extent.
Only four J-79 engines were tested, which was disappointing to
everyone, but this outcome was predictable given the fact that most of the
time spent in cell 48 was at the beginning of the month (July). It seems
that relatively few tests are usually conducted during the first part of
each month, while there is generally a rush at the month's end. The odd
schedule is a product of standard practice in the engine overhaul operation,
and is not really under the control of the engine test section at all. The
sampling equipment was removed from cell 48 beginning July 8, at which
point packing for the trip to Kansas City began.
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V. OPERATIONS AT TWA OVERHAUL FACILITY, KANSAS CITY
The test crew arrived in Kansas City, Missouri, on July 11, 1971,
and equipment setup began Monday, July 12. The TWA Overhaul and Test
facilities are located near the site of the new Kansas City International
Airport, about a 30-minute drive north of Kansas City. As was the case
in cell 48 at Kelly AFB, the entire layout was on one floor, which facilitated
preparations tremendously. The crew was experienced to such an extent
that the first engine test was run during the second shift on July 12, the
same day setup began. From the first day on, engines were tested at the
rate of over 2 per day.
Figure 17 shows the interior of cell number 5 prior to the installation
of instruments and probe. In this case, since the test cell was much smaller
than those at Kelly, the hydrocarbon analyzer's detector was located in the
pump room beside the rear of the cell. The probe mount was clamped to
the horizontal I-beams shown in Figure 18, and it was designed so that it
could be moved axially to accommodate the variety of engines to be tested.
The acoustic box for the HC detector is shown in Figure 19 as it was located
in the pump room, and Figure 20 shows the remaining analysis and readout
instrumentation. This latter group of instruments was located in the air-
conditioned control room, which made working conditions more pleasant
for the crew and no doubt added somewhat to the stability of the measure-
ments. The NOX analyzer shown in Figure 20 is the one furnished the
contractor by EPA, and the other chemiluminescent unit was left in San
Antonio. TWA personnel had indicated prior to the measurement operation
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Figure 17. Test Cell 5, TWA
Overhaul Facility, Kansas City
Figure 18. Exhaust Bellmouth and
Support Rails, Test Cell 3, TWA
Overhaul Facility, Kansas City
Figure 19. Detector Assembly of
Hydrocarbon Analyzer Installed
in Pump Room for TWA Testing
Figure 20. Analysis and Output
Instruments Installed in Control
Room for TWA Testing
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that at least 22 engines would be tested during the stay of the SwRI team,
and this number was surpassed early in the third week of the operation to
the delight of all concerned. The crew got a well-deserved trip home
during the weekend following the third week of tests.
Around the middle of the fourth week of tests, early in August, the
sample size for most of the engine types under test had reached acceptable
levels, so it was determined that certain additional tests would be valuable
if they would not interfere too greatly with TWA's operation. As they had
in the past, the TWA people proved both cooperative and Interested, and
several engines were run through additional scheduled runs to determine
the effects of a commercial smoke-suppressant fuel additive on gaseous
emissions. This objective was accomplished by running each engine first
on straight fuel, then on fuel treated with the additive at 0. 1% by volume,
and finally on fuel treated with the additive at 0. 025% by volume. Sample
line filters were retained after each of these tests, photographed for later
presentation in this report, and submitted to the sponsor as requested.
Other tests were run in which the engine was operated at several
throttle settings between idle and cruise (4 to 8 positions) to obtain a better
functional relationship between emission concentrations and some convenient
independent variable such as high-speed compressor rpm or percent of
maximum thrust. Again the cooperation of the host company, TWA, must
be acknowledged for allowing tests to be run which departed significantly
from their normal schedule. At the close of the 23rd operating day at TWA,
August 11, fifty-four tests (including repeats) had been run, and no engines
19
-------
were scheduled until 2nd shift August 12, so the test crew disassembled
the emissions measurement equipment, packed it, and began their return
to San Antonio.
VI. BRIEF DATA SUMMARY AND ANALYSIS
This section of the report summarizes data which are given in
complete form in Appendixes A, B, and C. Data on the fuels used for
testing at both Kelly AFB and the TWA facility are given in Appendix D.
A. T-56 Turboprop Engines, Kelly AFB
Emissions measurements were made on thirteen T-56 turboprop
engines at Kelly, 11 of which were T56-A7B models, one of which was a
T56-A15, and one of which was a T56-A7KB. The A7KB model was very
similar to the A7B in performance, but the A15 operated at considerably
higher maximum fuel rates, turbine inlet temperatures, and shaft horse-
power ratings. Table 2 presents a quick look at the emissions numbers
for the T-56 engines, with some values representing arithmetic averages
where identical modes were run on the same engine. The emissions values
for test 11 are for the sole T56-A15 tested, and they differ considerably
from those for the T56-A7 types. The hydrocarbon emissions measured
during tests 5 and 7 are different than the others in the power modes,
probably due to small oil leaks. The most interesting mode was the low
ground idle, which was the only mode run at off-design speed. Hydrocarbons
and CO increased manyfold during low ground idle, and NO2 became a major
portion of the NOX, generally 50% to 75%.
20
-------
TABLE 2. DATA C
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B. J-79 Turbojet Engines, Kelly AFB
Emissions tests were conducted on four J-79 turbojets at Kelly,
all of the J-79-GE-15 type. Some problems were encountered during the
first of these tests (test no. 14) with vibration, making it impossible to
obtain data except in idle modes. The data which were obtained are
presented summarily in Table 3, and once again some of the numbers
represent arithmetic averages of repeated modes. The same general trends
TABLE 3. DATA ON GASEOUS EMISSIONS FROM J-79
TURBOJET MILITARY ENGINES
Hydrocarbons (Wet), ppmC
Test
14
15
16
17
14
15
16
17
14
15
16
17
14
15
16
17
14
15
16
17
Idle
96
168
93
128
308
370
338
363
1.45
1.44
1. 52
1. 50
11
13
10
10
6
10
7
4
Military Normal Rated
0
1
0
CO (Wet),
23
23
13
C02 (Wet),
2.77
2.85
2.92
NOx(Wet),
77
76
80
NO (Wet),
70
71
72
0
1
1
ppm
29
43
29
%
2. 75
2.68
2.78
ppm
68
61
64
ppm
62
56
58
75%
1
0
1
44
38
43
2. 33
2.19
2. 37
43
36
37
39
32
32
22
-------
exist in these data which were in evidence in the T-56 data, namely relatively
high concentrations of CO, hydrocarbons, and NC>2 at idle, plus a fairly
smooth relationship between NO and thrust. The J-79 engine is a variable-
speed engine, unlike the T-56 which operates at constant speed when
producing work. The "Military" mode shown is "cold", that is, without
the afterburner. No attempt was made to sample exhaust gases while the
afterburner was in operation.
C. Commercial Turbojet and Turbofan Engines, TWA, Kansas City
Six types of engines were tested at TWA, and 54 engine tests were
conducted in all. By far the most widely tested engine was the JT8D-9 (18
tests), a modern turbofan model with internal bypass. Table 4 presents
data on 16 of the 18 JT8D-9 tests, and the other two will be presented later
since they contained additional operating modes between idle and cruise.
As noted at the bottom of Table 4, a smoke suppressant fuel additive was
used during Test 53 to evaluate its effects on gaseous emissions. The
results of this analysis will be reported in a later section of this report.
The trends of the emissions from the JT8D-9 engines tested were
similar to those observed for military engines and other commercial engines,
although the baseline hydrocarbon and CO levels were quite low by comparison
to most of the other types of commercial engines. In contrast to the lower
HC and CO levels, the NOX levels at high power conditions were rather high,
and both effects probably resulted in part from the use of smokeless burner
cans in the JT8D-9.
The JT8D-1 and JT8D-7 engines are very similar, and for the
purposes of this project they were considered as a single engine type.
23
-------
TABLE 4. DATA ON GASE0US EMISSIONS FROM JT8D-9 COMMERCIAL tURBOFANJENGINES
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In all, 7 tests were run on JT8D-1 & -7 engines, 6 of which were on the
standard format and are presented in Table 5. The other test, number 65,
TABLE 5. DATA ON GASEOUS EMISSIONS FROM JT8D-1
AND JT8D-7 COMMERCIAL TURBOFAN ENGINES
Test Number 22 32 44 50 66 67
Mode
Cruise
M.E. T. O.
Takeoff
Idle
Reverse
Mode
Cruise
M. E.T. O.
Takeoff
Idle
Reverse
Mode
Cruise
M. E. T. O.
Takeoff
Idle
Reverse
Mode
Cruise
M. E. T. O.
Takeoff
Idle
Reverse
Mode
Cruise
M. E. T. O.
Takeoff
Idle
Reverse
Hydrocarbons (Wet), ppmC
4
4
5
152
10
32
15
6
474
22
1
0
0
140
21
17
13
302
5
1
0
97
CO (Wet),
17
11
8
231
1
0
0
202
1
ppm
16
13
12
394
13
0
0
0
110
43
37
23
397
0
0
0
0
80
42
35
31
388
CO2 (Wet), %
2
2
2
1
3
.63
. 72
.98
.95
. 19
56
67
84
11
87
50
63
81
3
80
2. 72
2.93
3. 12
1.61
89
110
123
13
83
104
121
4
2.72 2
2.95 2
3.05 3
1. 54 1
3
NO^ (Wet),
60
79
100
11
NO (Wet),
57
75
95
5
.80
.96
. 07
.59
. 12
ppm
66
89
110
11
109
ppm
61
84
105
4
104
2.71
2.91
3. 10
1.68
53
70
88
14
50
67
83
9
2.76
2.96
3. 17
1.70
57
74
90
16
54
69
86
7
25
-------
included 4 additional modes between idle and cruise, and it will be discussed
in the next report section.
The emissions from the JT8D-1 and JT8D-7 differed from those of
the JT8D-9 somewhat, but not greatly, reflecting the basic similarity in
the JT8D family of engines. The most significant differences occurred
at idle, where hydrocarbons averaged 117 ppmC for the -9 against 130
ppmC for the -1 and -7 and CO averaged 296 ppm for the -9 against 365
ppm for the -1 and -7. In the takeoff mode, the average NO concentration
x
for the -9 was 121 ppm, compared to 99 ppm for the -1 and -7. All these
differences could conceivably be due to the use of smokeless combusters in
the JT8D-9 instead of the older version used in the JT8D-1 and -7. The fuel
used during test 66 contained the smoke-suppressant fuel additive mentioned
earlier at 0. 1% by volume and test 67 contained this same material at
0. 0125% by volume.
The tests run on JT4A-11 turbojet engines numbered 8 in all, and
seven of them are summarized in Table 6, with analysis of the eighth one
to be conducted in the next report section. The JT4 family of engines is an
older design than the JT8 family, and combustion in the JT4 was not as good
at idle as in the JT8, but the peak NOX values in the JT4 were lower.
Two of the JT4A-11 tests, numbers 55 and 56, were run with the
smoke suppressant additive in the fuel at 0. 1% and 0. 0125% by volume,
respectively.
Ten emissions tests were conducted on JT3D-3B engines, another
older type, but this time a turbofan with external bypass. The last 2 tests
26
-------
TABLE 6. DATA ON GASEOUS EMISSIONS FROM JT4A-11
COMMERCIAL TURBOJET ENGINES
Test Number
Mode
Cruise
M. E. T.O.
Takeoff
Idle
Reverse
Mode
Cruise
M.E. T. O.
Takeoff
Idle
Reverse
Mode
Cruise
M. E.T. O.
Takeoff
Idle
Reverse
Mode
Cruise
M. E. T. O.
Takeoff
Idle
Reverse
Mode
Cruise
M. E. T. O.
Takeoff
Idle
Reverse
26
29
34
49
54
55
56
Hydrocarbons (Wet),
1
0
0
800
2
22
19
17
453
16
2.43
2. 76
2. 82
1. 25
2.69
57
77
97
8
78
1
0
0
735
2
29
25
25
384
33
2. 18
2. 53
2.94
1.19
2.71
52
70
100
8
81
4
1
0
736
2
CO
27
22
17
473
21
COz
2. 18
2.49
2. 83
1. 26
2. 83
NOX
51
64
90
7
90
0
0
0
850
1
(Wet), ppm
32
29
26
412
29
(Wet), ppm
2. 22
2.46
3.00
1.22
2.88
(Wet), ppm
55
68
106
9
94
ppmC
1
0
0
870
2
25
22
22
464
22
2. 30
2.49
3.08
1.35
2.97
54
65
102
9
95
1
0
0
929
2
39
33
23
483
28
2. 25
2.41
2.99
1. 35
2.96
48
62
100
9
96
1
0
0
774
1
30
26
25
463
27
2. 30
2.53
3.05
1.45
3.05
50
62
98
9
97
NO (Wet), ppm
54
75
95
3
76
47
65
95
2
76
49
61
88
3
86
51
64
103
3
90
50
62
100
3
93
46
58
97
3
94
46
57
95
3
94
27
-------
on JT3D-3B engines were of extended duration with extra modes to obtain
a map of the engine's emissions, and they are treated in the following
report section. The other tests are summarized in Table 7, and it should
be noted that the hydrocarbon data omitted from Tests 62 and 63 were
excluded because an oil leak masked the true emissions values. In addition,
these same two tests were the ones during which the fuel contained the com-
mercial smoke suppressant additive at 0. 1% and 0. 0125% by volume,
respectively.
The JT3D-3B engines produced high concentrations of hydrocarbons
and CO at idle, but generally less NOX than the more modern engines.
The sixth mode (1. 37 EPR) was peculiar to the standard test sequence for
the JT3D-3B.
Several tests were run on JT3C-6 engines early in the TWA tests,
but it should be noted that these engines were destined to be sold out of the
United States by TWA rather than placed back in domestic service. The
JT3C-6 is a turbojet engine of a relatively old design, and the results of
the tests on this engine are given in Table 8.
The other type of engine tested at TWA was the CJ-805 turbojet,
unique in the TWA fleet because it was made by General Electric rather
than Pratt & Whitney and because it was the only single rotor engine tested.
The gas generator of these engines is physically similar to that of J-79
military engines, although the emissions from the two types of engines are
somewhat different. Table 9 presents emissions data on CJ-805 engines,
and it should be noted that the fuel used during tests 58, 59,and 60 contained
28
-------
TABLE 7. DATA ON GASEOUS EMISSIONS FROM JT3D-3B
COMMERCIAL TURBOFAN ENGINES
Test Number
Mode
1. 37 EPR
Cruise
M. E. T. O.
Takeoff
Idle
Reverse
Mode
1.37 EPR
Cruise
M. E. T. O.
Takeoff
Idle
Reverse
Mode
1.37 EPR
Cruise
M. E. T. O.
Takeoff
Idle
Reverse
Mode
1.37 EPR
Cruise
M. E. T. O.
Takeoff
Idle
Reverse
Mode
1. 37 EPR
Cruise
M. E. T. O.
Takeoff
Idle
Reverse
27
28
41
48
51
61
62
63
Hydrocarbons ,
52
65
68
1060
70
72
76
77
93
1380
80
1
12
3
0
1025
20
4
0
0
0
910
0
ppmC
12
2
0
0
710
0
26
26
26
16
1240
CO, ppm
26
20
14
658
11
22
37
13
10
692
13
43
20
9
8
649
12
43
18
9
5
583
6
52
26
15
25
645
20
47
25
12
11
627
66
34
16
11
674
72
53
26
22
675
CO? (Wet), %
1.60
2. 04
2. 51
1.39
2.44
32
50
75
7
75
27
44
71
0
70
1.45
1. 78
2.08
2. 58
1. 38
2.51
26
40
61
97
7
78
22
37
58
93
1
75
2. 09
2.27
2.49
2.77
1.49
2.69
NO
38
49
75
91
9
81
NO
36
47
74
91
2
80
2. 16
2. 34
2. 58
2. 88
1. 80
2. 80
Y (Wet),
38
49
65
93
10
81
2. 21
2.44
2.65
2.89
1.80
2.81
ppm
37
50
65
87
8
79
2.24
2.48
2.69
3.01
1.68
35
46
61
85
8
2. 22
2.48
2.68
2.99
1.66
33
44
58
80
8
2.26
2.47
2. 70
3.02
1.62
30
47
62
86
9
(Wet), ppm
30
43
61
89
3
76
34
45
62
85
4
76
33
43
57
83
3
31
42
55
77
4
29
45
59
83
4
29
-------
TABLE 8. DATA ON GASEOUS EMISSIONS FROM JT3C-6
COMMERCIAL TURBOJET ENGINES
Mode - Cruise M. E. T. O. Takeoff Idle Reverse
Test
19
23
40
Test
19
23
40
Hydrocarbons (Wet),
17
24
0
45
38
38
2. 10
2. 17
2. 23
42
43
52
33
43
46
11
19
0
CO (Wet),
50
8
28
C02 (Wet)
2.31
2.38
2.34
NOX (Wet)
49
48
58
NO (Wet),
43
47
55
11
13
0
ppm
28
5
11
, %
2.66
2.67
2.76
, ppm
74
70
73
ppm
71
69
73
ppmC
1433
1930
2160
706
768
714
1. 30
1.40
1. 53
7
6
8
1
3
2
16
13
33
23
2. 35
2. 49
55
58
51
57
30
-------
TABLE 9. DATA ON GASEOUS EMISSIONS FROM CJ-805
COMMERCIAL TURBOJET ENGINES
30
31
33
39
57
58
59
60
Test Number
Mode
Cruise
M. E. T. O.
Takeoff
Idle
Mode
Cruise
M. E.T.O.
Takeoff
Idle
Mode
Cruise
M. E. T. O.
Takeoff
Idle
Mode
Cruise
M. E. T. O.
Takeoff
Idle
Mode
Cruise
M. E.T.O.
Takeoff
Idle
a smoke-suppressant additive at 0. 1%, 0. 0125%, and 0. 1% by volume.
respectively. Test 60 was a repeat of test 58, run because some problems
developed with the additive pump during test 58, leading to some uncertainty
about the accuracy of the additive concentration.
Hydrocarbons (Wet), ppmC
2
0
0
302
57
48
45
464
4
0
0
353
52
43
43
397
0
0
0
488
52
44
38
552
0
0
0
325
CO (Wet),
60
51
48
573
0
0
0
340
ppm
52
48
46
472
0
0
0
337
68
67
60
454
0
0
0
345
56
54
53
471
0
0
0
372
65
64
65
492
C02 (Wet), %
2.51
2. 70
2.89
1.63
59
69
82
9
53
62
74
1
2.34
2.62
2.91
1. 52
57
71
87
8
52
64
81
1
2.54
2.59
2.90
1.56
60
64
83
8
54
59
77
2
2. 58 2
2.63 2
2.90 2
1. 77 1
NOX (Wet)
53
57
84
11
NO (Wet),
51
55
81
3
.55
.70
.96
. 31
, ppm
60
66
81
7
ppm
53
61
75
3
2.61
2.71
2.97
1. 30
58
63
80
8
55
61
75
3
2.56
2. 75
3.00
1.43
61
66
81
7
56
61
75
3
2.53
2. 70
2.98
1.38
54
61
75
8
50
57
71
2
31
-------
To summarize and complete this section of the report, Table 10
has been prepared to compare average emissions from the 6 types of
TABLE 10. COMPARISON OF BASELINE GASEOUS EMISSION FROM
SIX TYPES OF COMMERCIAL ENGINES IN FOUR COMMON MODES
Engine
JT8D-9 JT8D-1 & -7 JT4A-11 JT3D-3B JT3C-6 CJ-805
Average Hydrocarbons (Wet), ppmC
Mode
Cruise
M. E. T. O.
Takeoff
Idle
1
1
1
117
2
1
1
130
1
0
0
813
Average CO (Wet),
Mode
Cruise
M. E. T. O.
Takeoff
Idle
Mode
Cruise
M. E. T. O.
Takeoff
Idle
Mode
Cruise
M. E. T. 0.
Takeoff
Idle
17
14
10
296
2. 55
2. 76
2.99
1.65
67
90
121
11
28
21
16
364
Average
2.72
2.90
3.08
1.68
Average
64
82
99
13
29
25
22
447
C0? (Wet),
2. 27
2. 52
2.96
1. 30
NOY (Wet),
52
67
99
8
28
28
29
1054
ppm
30
15
13
650
%
2. 23
2.49
2.83
1.60
ppm
45
62
87
8
14
10
8
1678
40
29
15
720
2. 17
2.34
2. 70
1.36
46
52
72
7
1
0
0
358
58
52
50
484
2. 53
2.68
2.94
1.49
58
65
82
8
Average NO (Wet), ppm
Mode
Cruise
M. E. T. O.
Takeoff
Idle
63
85
115
4
59
77
95
5
49
63
96
3
41
59
84
3
41
48
71
2
53
60
76
2
32
-------
commercial engines tested in 4 operating modes. All the tests are
averaged in except those which included extra operating modes (64, 65,
68, 69, 70, 71), and only the four test modes common to all the engines
are retained for comparison (cruise, M. E. T. O. , takeoff, and idle). It
should be noted that dilution occurred during idle modes when the internal-
bypass turbofan engines (JT8D types) were sampled with the standard
probe. This outcome made it necessary to correct idle emissions on
Tests 44 and 45 for the dilution with bypass air, and the other JT8D engines
were sampled with a center line probe having four ports during the idle modes
to prevent dilution.
D. Effects of a Commercial Smoke-Suppressant Fuel Additive and
Emission Maps for Four Types of Commercial Engines
All the engine tests at TWA up to and including number 52 were run
on fuel containing no additives for smoke suppression. This procedure
was followed at the request of EPA and SwRI so that emissions could be
measured under flight conditions rather than test cell conditions, but the
effects of the normally-used additive were of interest to the sponsor, also.
To obtain the desired information, the TWA test personnel agreed to run
several engines two or three times each, with and without the additive in
the fuel. The data resulting from these tests are presented in Table 11,
and although no comprehensive analysis has been performed, it appears
that the presence of the additive in the "normal" concentration (0. 1% by
volume) may be associated with small increases in hydrocarbons and CO
and a small decrease in NOX. The effects of the additive on smoke were
obtained qualitatively by recovering sample line filters from each of the
33
-------
TABLE 11. COMPARISON OF^GASEOUS EMISSIONS USING UNTREATED AND ADDITIVE-TREATED FUELS
£*,»{>«
T.&-V |j
.% A4TS
52 S3
O O-1
: '
' j i .
_.:... _IQ
... _.
I'fc'T
i ! O
O
o
v 9.4
1 I
\ ^
( i
..i LB
\ 9
\ 5
345
2. , ,
: : i ; i . i
; i ; . .
:
U.A.9
_:_._. .5
>\
.89
\ \ 9
5
JT4A~IU CJ-BOS ; -rvSD-JSS, '-j-V^O-\
54 SS
O 0. I
0
0
2
1
O
0
9 29
2
25
2.2
2-Z
4 fo 4
2 Z
zi-i 9
2.97
!"'."":> 3
483
28
2.2 5
2.41
2.99
1.35
2.9 VsV""1*
54
(b 1
75
Q> \
(ofc
~r 7
JE.T) jTt>'««
50
57
7 1
2
S!fe
\
.75
3
. .".. 2.C,
It
11 4O
O-l O-0»?5 O O.\ Q.C)I25
. j. ...: _
2S
V 2
. \ \
;
If
2.9
-------
tests listed in Table 11. These filters were submitted to the sponsor as
requested after being photographed for documentation.
Figure 21 shows filters used under identical conditions except for
the additive in tests 52 and 53 (left-to-right) on a JT8D-9 engine. The
test numbers labeled on the petri dishes refer to TWA tests only, that is,
they are in a sequence beginning with "1" for the first test at TWA.
Figure 22 shows filters used in tests 54, 55, and 56 (left-to-right) on a
JT4A-11 engine, and Figure 23 shows filters used during tests 57, 60, and
59 on a CJ-805 engine, respectively (left-to-right). Figure 24 shows filters
collected after runs 61, 62, and 63 on a JT3D-3B engine (left-to-right), and
Figure 25 shows filters from runs 65, 66, and 67 on a JT8D-1 engine (left-
to-right). In addition to the fact that the additive did appear to reduce sample
soot content somewhat in proportion to its concentration, the filters show
graphically the effect of the smokeless burner cans in the JT8D-9 as compared
to the similar JT8D-1 which has the old-style combustors.
The remaining special tests involved "mapping" several types of
engines at a number of conditions between idle and cruise. These tests
were initiated because there are large jumps in CO, hydrocarbons, and
NOX between idle and cruise, and it was desired to fill in the curves bet-
ween the two conditions. Figures 26 through 30 illustrate the trends ob-
served during 5 of the 6 mapping tests. The test not presented graphically,
number 64, was the first mapping conducted and did not include a suf-
ficient number of points between idle and cruise. Data from test 64 can
35
-------
Figure 21. Filters Used During
Tests on a JT8D-9 Engine
Figure 22. Filters Used During
Tests on a JT4A-11 Engine
Figure 23. Filters Used During Tests on
a CJ-805 Engine
36
-------
Figure 24. Filters Used During Tests on
a JT3D-3B Engine
Figure 25. Filters Used During
Tests on a JT8D-1 Fngine
37
-------
400
300
OJ
QO
q 200
o
voo
0L
80
K
O
-2
2
O
&
s
Q
RGORE
FOR.
("1
-------
500 r
OJ
400
2. i°°
o
f-
-2
u»
-D
-------
500 r
400 -
3*00
°0
\00
20O
ISO
O
2
t
0
140
ioo
21 80
o
-------
X
-------
VO r
*
o
.
-fl, S
,0. JX-
.- o
I
0 O
*
o JL
8 -
<0
o
i/t
d
i
LU
Lil
O
O
VO
\4-
3O
MAP
-------
be found in Appendix C along with basic data on all the other commercial
engine tests.
As shown in Figures 26 through 30, emission levels vary consid-
erably among engine types at a given power setting, but the trends in
emissions from all engines tested as a function of thrust are similar.
Hydrocarbon and CO emissions seem to approximate hyperbolic curves,
and oxides of nitrogen seem to follow an exponential function of thrust
with exponent between 1 and 2. This very brief look at emissions as
functions of engine operating mode is not intended to be definitive, but
only introductory. It may be convenient to use some other independent
variable if empirical equations are to be determined, such as percent
of maximum thrust or percent of N, or N£ rpm, since such variables
lend themselves better to grouping of data from several types of engines.
VII. SUMMARY AND COMMENTS
The research program on which this report is based was com-
pleted in less than 90 days as required to fulfill a short term need for
baseline aircraft turbine emissions data, but the brevity of the effort
makes the information and experience gained no less significant. The data
collected in this phase of the overall EPA data acquisition effort are given
in complete form in Appendixes A through C, and summaries are presented
in section VI.
Appendix D of this report contains the results of analyses run
on fuel samples from Kelly AFB and from TWA. The fuel used at Kelly
was a JP-4 test fuel, and although the fuel used at TWA was colloquially
43
-------
called a JP-4, it was in fact Mobil Jet A, a heavier fuel with a higher
boiling range. A sample of the fuel used at TWA was sent out to an
independent laboratory about midway in the test period for H/C ratio
analysis, and the result which came back was 1. 722, a surprisingly low
figure. Another sample was sent which was drawn personally by the
supervisor of the SwRI test crew, and the H/C ratio obtained was 1. 968,
a much more realistic value. It has been concluded that the results from
the initial sample should be discarded, since that fuel must have been con-
taminated somehow. The H/C ratio of the JP-4 fuel used at Kelly AFB was
1.995-
One of the most serious problems encountered in conducting this
investigation was repeated structural failure of the exhaust sampling
probes. The design used was straightforward and relatively inexpensive
to render in metal, but even after having been extensively reinforced it
was no match for its environment. Another problem encountered with
the 12-point probe was its tendancy to inhale bypass air as well as sample
when used with internal-bypass engines such as the JT8D. This effect
was most pronounced at idle, and the problem was finally circumvented
by using a centerline probe of smaller diameter and having four sample
ports during idle modes. Upon considering these problems, it seems
that a prerequisite to any further aircraft turbine exhaust sampling
should be the design of an adequate probe.
The instrumentation used during this program proved quite satis-
factory, especially the new FIA hydrocarbon instrument and the chemilu-
minescent NOX analyzer. A long-path NDIR for CO measurement and a
44
-------
new NDIR CC>2 analyzer would have been desirable, but could not be
obtained within the lead time available. The continuous readout provided
by the 4-pen recorder permitted constant monitoring of emissions and
the ability to examine transients. The EPA aircraft emissions program in
general has added to the technology required to measure emissions from
turbine-powered equipment and other low-emission sources, and this
experience should be valuable to other studies of air-, land-, and water-
based transportation systems.
45
-------
APPENDIX A
Data, on Emissions from T-56
Turboprop Engines
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 1
Date 6/17/71 Location Kellv AFB. Test Call
Engine serial No. AE-102635
Engine type T56-A7B
Engine total time, hours Not Recorded
Time (hours) since:
Hot section overhaul
0
Fuel
High-speed compressor overhaul
First stage nozzle guide vane overhaul
High-speed turbine overhaul N. A.
JP-4 Test Fuel Additive and concentration
Low-speed compressor overhaul 0
N* A. Combustor can replacement
Low-speed turbine overhaul 0_
N. A.
Inlet air humidity, Ibm H_O/lbm dry air
Relative humidity 52%
0.0186
Start.
Inlet air temperature, °F 91
Atmospheric pressure, in Hg 28. 93
Finish
90
28.93
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO;> (wet), ppm
NOX (wet), ppm
75% I 100% 1 Mil.
0:00 _ !5:0p_ JlQiSp .
2295**! 3238**j 3502**
13, 800113, 800113, 800
~- -4- - f-
1450 ! 1 800 ! 1915
30.0 30.0 i30~o"'
0". 0134 0. 0167 '0.0177
1510 1700 1780'
31 28 26
2. 57 3. 06 3. 29.
0 0 ;0
81 115 ,124
Fit. Idld Accel. Fit. Idl«i L. G. I.
1.5:00 '18:00 19:50. 21:00
1 I
13, 300 1J JJOO : 1 3 ,. 400. ^.9.50 .... .
820 f2050 i810 1560"
H. G. L \
24:00 ;
j :
13.300J ;
?Q5 i j
27.9 bo". 8 28.4 14.7* 27.9
6. 0082 |0."0185 ;0. 0079 0. 01064 0.0070 ~
1 : i ...-
! ; j :
1128 |l860 1120 1150 ' 1050
i j .
28 24 28 .J2&7 _ 30. __ , .__
1.55 |s. 74 1.57 2. 13 . 1.40 I .....
o ;o 'o ^352 :
32 127 32 'J28 26
*Mfr's. airflow data not available at this N}, so (F/A) was calculated from exhaust composition
subsequently used with measured fuel rate to calculate air flow.
**Observed power was back-calculated because only corrected power was recorded during run.
and
i
NJ
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No.
Date 6/18/71 Location Kellv AFB. Test Cell 56
Engine total time, hours 5114
Engine serial No. AE-103141
Time (hours) since:
Hot section overhaul 0 Low-speed compressor overhaul Q
High-speed compressor overhaul N. A. Combustor can replacement
Engine type T56-A7B
0
0
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul N. A.
JP-4 Test Fuel Additive and concentration
Low-speed turbine overhaul 0_
N. A.
Inlet air humidity, Ibm H jO/lbm dry air
Relative humidity 63%
0.0214
Inlet air temperature, ° F
Atmospheric pressure, in Hg
Start Finish
80 80
29. 26 29. 26
Mode
75% : 100% I Mil. IFlt. Idle! Accel. Fit. Idle H. G. I.! L. G. I. <
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
0:0.0
2325
.5:3Q_....lUiQO .116:30 ;19:30 21:30 ,24:00 [26:30
; i : i
, i j i . .. ; : ..
3202 13553 J865 J3684 >865 277 1119
13, 800~13, 800|i^'^0q|l3, 300]l4, 2jOO il3^ 300 J13, 430 J9, 980
1 I ^ I i
1465 :1810 11945 J910 11980* '905 J715 J555
J29.2 ilS.O*
30.8 30.8 '30.8 i28. 7 132.6 28.7
0. 0132 0. 0163 0. 017510. 008810. 0168 0. 0088 iO. 0068 0. 0103*
I .j . : I _ .
i j ! | I
1505 1710 1780 ;1168 1900 H170 1046 1128 "
CO (wet), ppm
COZ (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NOg (wet), ppm
NOX (wet), ppm
28
2.37
0
68
26
3.08
0
96
|24
J3.28
JO
102
'1.66
32
1 i i
23(min)30 _J27 |271
3. 54^°;!. 64 il.32 12.07
!102
15
32
4
!225
25
*Mfr's. airflow data not available at this N,, so (F/A) was calculated from exhaust composition
and subsequently used with measured fuel rate to calculate air flow.
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 3
Date 6/18/71 Location Kelly AFB. Test Cell 56
Engine type T56-A7B
Engine serial No. AE-104886
Time (hours) since:
Hot section overhaul 0
Engine total time, hours 4865
0
Low-speed compressor overhaul
High-speed compressor overhaul N. A. Combustor can replacement
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul N. A.
JP-4 Test Fuel Additive and concentration
Low-speed turbine overhaul 0_
N. A.
Inlet air humidity, Ibm H^O/lbm <
Relative humidity 52%
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, ° F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm
NOX (wet), ppm
Irvair 0.0186
75% l 100%
0:00 '4:00
Inlet air temperature, 8 F
Atmospheric pressure, in H
Mil. Fit. Idle1 Accel. Fit. Idl4 H. G.'l.
9:00 115:00
! _-U j
2193 3070 [3421 "JP1
13,780} 13,800
1430 ~1755
30. 1 30. 1
OTO~i3TO; 0162
1506 ', 1710
. _ ..
40 39
2.42 3.07
0 : 1
73 103
13,800|13,280
T885 [875
30.1 {28. 0
H 0:0174! 0.008 7
t .
__._L
1780 [1178
1
!
. !
39 j45
3.25 11.60
- -
1 2
111 33
1.7:00 18:00 .20:00
: 1
Start Finish
90 88
2 29.27 29.27
L. G. I. i
22:30 . I
3808^821 2~99 111 9
"14, 200 13728bji3,44oT9f 970 "
-traax)-; -
2055M880 4705
3T"."8Cr«)28."6" "12175
070T80 JO. 0087 JOV 0069
]
iVTo 1182 ]l062 "
(max) "
t "I"
38(min!45 |45
3.48I"») 1.62 jl.30
O(min) 2 12 ~
._.. ' . _ . : ( .......
: J
565
1574*"
0~."<5"102* ~~
1166 _
289
2.05
228"
'" ' -- T' " ' ' "*-
HlW)r33 ' 24 ' 26 |
^ _ A *- " .^_. '
*Mfr's. airflow data not available at this NX, so (F/A) was calculated from exhaust composition
subsequently used with measured fuel rate to calculate air flow.
and
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 4
Date 6/18/71 Location Kellv AFB. Test Cell 56
Engine serial No. AE-101854
Time (hours) since:
Hot section overhaul 0
Engine type T56-A7B
Engine total time, hours 7793
Low-speed compressor overhaul
Fuel
High-speed compressor overhaul N. A.
First stage nozzle guide vane overhaul _
High-speed turbine overhaul N. A.
JP-4 Test Fuel
.Combustor can replacement 0_
Low-speed turbine overhaul 0_
Additive and concentration
N. A.
Inlet air humidity, Ibm HgO/lbm dry air 0.0187
Relative humidity 59%
Start
82
Finish
81
Inlet air temperature, °F
Atmospheric pressure, in Hg 28. 90 28. 90
Mode
75% j 100%
Mil. iFlt. Idle Accel. Fit. Idle H. G. Ij L. G. Li
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, No
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, ° F
Exhaust gas pressure, psia
0:00
10:50 116:35 (24:20 -26:05 26:35 ;27:50 30:50
22!4.__, 13092. . J33_99__l823 13618 |821
13, 80013, SOOs, 800TiV, 300
14,240 i!3, 270
87 j.,..
9^.940. j I
1440 1770 11910 |890 [2000 1895 ?05_
3^.8 2.30-8 il°-8ZJ28-7 i32/6 -28. 7 'J28." 1
070T30~0. 6l6"OrO. "6T72~]d. 0086 670170 fa. 0087 ft.0070
14.J9* ;
'
1510 1710 ,1780 11180
1890 ;1180 11052
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm
NOX (wet), ppm
32
2. 38
0
61
5
66
2.98
0
3.21
!1.67
""1
iO
1
90
3
J101
31
K) |33
3. 60(«*.)|1.67
0 p
?5 25
5
30
. 33.
.
O
18
"
1155 I
300
1348
I"'
*Mfr's. airflow data not available at this N^, so (F/A) was calculated from exhaust composition and
subsequently used with measured fuel rate to calculate air flow.
i
in
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 5
Date 6/21/71 Location Kelly AFB. Test Call 56
Engine type,
T56-A7B
Engine serial No. AE-101776
Engine total time, hours 7751
Time (hours) since:
Hot section overhaul
0
Low-speed compressor overhaul 0_
High-speed compressor overhaul N. A.
.Combustor can replacement 0.
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul N. A.
JP-4 Test Fuel
0
Low-speed turbine overhaul 0_
Additive and concentration N. A.
Inlet air humidity, Ibm H-O/lbm dry air 0.0184
Relative humidity 67%
Start
Inlet air temperature, °F 83
Finish
83
Atmospheric pressure, in Hg 29. 21 29... 21
Mode
75% I 100% i Mil.
Ml Accel. Fit. Idl H. G. I L. G. I.-;
.
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
0:00
.5:00 i.l_0_;3Q. Jl5:3Q 18:30 19:30 21:00
2259 " "3202 i 3531
13/820] 13, 80p[l3, 800
838
JL*J^5!838_""" '232
1450 '1795 11925 J900
30.6 30.6 i30.6 J28. 0
lit iPJLi14i_200.. I1A. .y £
2010 885
. 6
13.,_320
685..
28.5
0. 0132~0. Ol6~3,0."6l75 JO. 0089 io. 0172 0. 0089 0, 0067,
i i
_ I I ! _
1505 1705 '1780"_ ":1180 jl850*"') 1175 :1040~
2.3:0.0 ;
.9_4___ i
9^840. [
i
55jfl'_f
o.olis*
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO£ (wet), ppm
NOX (wet), ppm
*Mfr's. airflow data not available
subsequently used with measured
3 1
26
;23
127
2.1
11
2. 54 .3. 17 J3. 42 .. 1. 6.7 |3,.64^1. 70 . |l.
42
64
5
69
46
93
2
95
4.4
.U02
3
1105
;37
31
46
. 3.15
26
at this Nj, so (F/A) was calculated from exhaust composition and
fuel rate to calculate air flow.
.>
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 6
Date 6/21/71 Location Kelly AFB. Test Cell 56
Engine type T56-A7B
Engine serial No. AE-104313
Engine total time, hours 6027
Time (hours) since:
Hot section overhaul 0 Low-speed compressor overhaul 0
High-speed compressor overhaul N. A. Combuetor can replacement
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul N. A.
JP-4 Test Fuel
0
Low-speed turbine overhaul.
Additive and concentration N. A.
Inlet air humidity, Ibm H ,O/lbm c
Relative humidity °°%
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, ^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gasjpressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO£ (wet), ppm
NOX (wet), ppm
Irv air 0.0176
75% !100%
0:00 .6:30 ...
2456 3355
13/86b]l 3/800
1510 ;1865
31.^2 ;31.2
1510 1712"'"
40 26
2.52 3.10
0 :0
63 90
9 8 "
72 98
*Mfr's. airflow data not available at this Nj, so
Inlet air temperature, °F
Atmospheric pressure, in H
Mil. Int. Idlej Accel.
10:3.0 117:30 119:00.
i
_ I
3662
13,800
834
13, 100
1980 J895
..
31.2 |28. 1
0/6176 0/0088
" "" ;
... __ . J.
1775
21
3. 34
o ""
97
_._.
104
\LL46
25
1.60
0
24
5" """
29
Fit. Idl^ H. G. I
21:00 .J22:OQ
i
37285nN|840 ]241
14-220
CWa^iT
(.wvajc)
2045
13,200
r
870 """
33. 0 ;28. 6
0.0172 JO. 0084
i Q £* r\
L O O \Jf \
17] min)
3. 74r-V)
13,420
720
29.5
076668"
1132 (1026
" 1 ' ' "'
24
1. 58
o i fc ~;. ;
1
b
1.26
0
17"
s -
23
Start Finish
74 74
B 29. 19 29. 19
I,. G. T]
24:00 ;
111 !
9/980
550
f
il- JL* L. _I
1084 j
217
1.94
250
f"
15"
22
1 ' "
1
(F/A') was calculated from exhaust composition and-
subsequently used with measured fuel rate to calculate air flow.
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 7
Date 6/22/71 Location
Engine serial No. AE-101889
Time (hours) since:
Hot section overhaul Q_
Kellv AFB. Test Cell 56
Engine total time, hours 8488
Engine type,
T56-A7B
Low-speed compressor overhaul
High-speed compressor overhaul N. A.
.Combustor can replacement 0
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul N. A.
JP-4 Test Fuel
Low-speed turbine overhaul 0_
Additive and concentration N. A.
Inlet air humidity, Ibm HJO/lbm dry air Q.Q1QQ
Relative humidity 72%
Start
Inlet air temperature, ° F 83
Finish
83
Atmospheric pressure, in Hg 29. 01 29. 01
Mode
75% I 100%
Mil.
Fit. Idle! Accel. Fit. Idle1
H. G. I.:
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
_- .in..,...- .,, -*t --*. imm '. .iiiiii.iiiMiiiBi .in. -in.iinI. -^P
0:0.0. 7:35
13.1.35. 19:.35 |21:37 22:15 .123:15....
2281 ;3180
3487
840
13,800113, 800
13, 800*13, 240
3510 1820
118
24:50.
328
14,260113,250 9,910
13, 3301
1480 ;i825 il9,60_. 890 J1.9J7.5 :895_ (5.75
3JLA_.J.3°rA..-.3JK6." j.28._2 j.32. 4_ ;28. 2 J14. 6*
0. 0134-.6.of66;q. 0178 JO. 0088)0. 0169 JO. 0088 jO..010.9.1
L5JO___J71p jl_780_..jl_l6.4_.. .].1858^a^1164l Iili30_._..]ibiT7L
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO^ (wet), ppm
NOX (wet), ppm
27
29 -.._ |
26 ... 24
2 . 53 ! 3 . 1 6 I 3 ._42. _4 1....7 1
43 '41 "f 41 ~ 141 .........
60 83 _" "|93 '_
7 ' "7'" ""^6" ......... ;
67
3. 76(-««)
42 ""
(29...
1.71
!42~"
20 Q
2. 15
.1?.
3_2_
45
90
99
32
100,
16
25
Ire-
*Mfr's. airflow data not available at this Nj, so (F/A) was calculated from exhaust composition
subsequently used with measured fuel rate to calculate air flow.
and
\
co
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 8
Date 6/22/71 Location Kelly AFB. Test Cell 56
Engine serial No. AE-101743
Time (hours) since:
Hot section overhaul 0
Engine type T56-A7B
Engine total time, hours
7032
High-speed compressor overhaul N. A.
Low- speed compressor overhaul
Combustor can replacement
First stage nozzle guide vane overhaul
High-speed turbine overhaul N. A.
Fuel JP-4 Test Fuel
0
Low-speed turbine overhaul 0
Additive and concentration
N. A.
Inlet air humidity, Ibm HJO/lbm dry air 0.0164
Relative humidity 49%
Start
90
Finish
90
Inlet air temperature, °F
Atmospheric pressure, in Hg 29. 08 29. 08
Mode
75% ; 100% Mil. 'Fit.
AcceL Fit. Idl^H. G. I.! T,. G. TJ
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, ^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, ° F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO£ (wet), ppm
NOX (wet), ppm
0:00 7iOO tl?LQ.Q U5:.QO
2105 ! 3004 i 3 355 1 840
13, 800;13, 800113, 800113, 240
17:52 19.:3.0 '21:00... 23iO.O ,
3533 " '1676"
j404 .14.2..
0 13,800113,240 14, 000 J13, 300 13,40019,930 i
__j._, ... -_.., .. _,_ . -^frn^rX" J i " - - \ I
1410 ;1755 .11880 J905
3! -50- 1 30. 1 127. 8
76.5 ,M5.__ : '.
28.4 115.3* i i
1845 .
30. 9__. ,28. 0
0.0130 0.0162*0. 0173 JO. 0090 0.0172 !0. 0084 0. 0075 i 0. 0106*
: ~::.;;_.:._L_Z i. _;:,! ..;i_i.:i::l:::::;::
1505 1710 ,1780 .1206 1900 !l!52 1094 |1178 i
' " - " - ' ' '- ' ' i~" . - -*- . « . - - j _.f.,_ .*. ... j ?eu . ^. . ( .. _
34.. .19 ..U3 . .Ii4_.
2. 35 .3. 00 !3._2.a L.6J_. J3.
0 :0 |0 JO '0
7l" 'l05j Jill ~ |27 _ i
8 6 " " ;5 !lO """]""
79 111 !l!8 j37 !l.
. 55
269
....3&. -L2.L4
215
I
28
[28
*Mfr's. airflow data not available at this Nj, so (F/A) was calculated from exhaust composition and
subsequently used with measured fuel rate to calculate airflow.
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No.
Date 6/23/71 Location Kellv AFB. Test Cell 56
Engine serial No. AE-101695
Engine type T56-A7B
Engine total time, hours 4828
Time (hours) since:
Hot section overhaul
0
Low-speed compressor overhaul
High-speed compressor overhaul N.A. Combustor can replacement
0
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul N- A.
JP-4 Test Fuel
0
Low-speed turbine overhaul 0_
Additive and concentration N. A.
Inlet air humidity, Ibm H-O/lbm c
Relative humidity 58%
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N2
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, ° F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm
NOX (wet), ppm
Iry air 0.0170
Inlet air temperature, ° F
Atmospheric pressure, in H
75% i 100% ! Mil. iFlt. Idlci Accel. K. G. I.' T,. G! I
0:OJ3 ,5:QQ_...-.LQiQQ..!l5:30
i ' I
2237 :3114 '3443 1651
13, 800 j 13, 800113,800113,230
1450 :1795 ! 1930 18 15
30. 5 30. 5 "js'oi'sT J28.0
0.01 3 2 ' 0 . Of 6 3 "q." 0176 fo . 008 f
1505 1710 1775 11132
i ;
j
42 35 ;30 J30
2.44 3.07 '3.28 11.67
4 :4 !2 J3
71 103 109 28
7 5 5 !4
78 108 '114 ,32
17:00 18:30 .
354?"m'l)|363
1 37800 T37~43(f
19J5 750 _
30. 5 28. 9
"6. Ol"77 !0. 0072
-
(._... ..__._
20:30 .
126
9,926""
14. 9* :"~
0. 01 05"
1760 1080 '1152
. . . -[ _ ~
^29fmin) 31. .
3,38^) 1.46
3 4
23
5
1170^,28
24)1
f2. 12
16?...
13
16
29
Start Finish
85 85
e 29.12 29.12
. T,. G. Ti T, C, T
22:00 29:30 |
J.?6__ !l_26__i
J?jJ?10 |?,900J __^
j
580 j 570 _ ]
15.0* J14. 6* ] '"
1 0 ._6_1 0 7PK) . 0 1 0.5*_.""____
1150 J1150 *"
270 J270
2,16 J2.19 4_
175 J171
i?. . !i2_ _rrr ""~
17 ;i7
29" " '29 I
*Mfr's. airflow data not available for this Nj, so (F/A)
subsequently used with measured fuel rate to calculate
was calculated from exhaust composition and
air flow.
O
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 10
Date 6/23/71 Location Kellv AFB. Test Cell 56
Engine serial No. AE-104192
Engine type T56-A7B
Engine total time, hours 5381
Time (hours) since:
Hot section overhaul 0 Low-speed compressor overhaul 0
High-speed compressor overhaul N. A. Combustor can replacement
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul N. A.
JP-4 Test Fuel
0
Low-speed turbine overhaul 0_
Additive and concentration N. A.
Inlet air humidity, Ibm H JO/lbm dry air
Relative humidity 37%
0.0127
Inlet air temperature, ° F
Atmospheric pressure, in Hg
Start Finish
93 94
29.05 29.05
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, ° F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NOg (wet), ppm
NOX (wet), ppm
75% 1 100% 1 Mil. !Flt. Idle! Accel. Fit. Idl4 H. G. I
0:00 5:00 i 10:00
j
2083 2939 ; 3216
15:30
720
13,9001 13, 880J 13,900} 13, 340
:
1405 ! 1740" i860 " j 860
29.9 29.9 29.9 28.0
0.0131 0.0162 0.0173
1508 1710" 1782""
44 .29 .. 24
2.39 3.02 .3.22 _
0 0 0
73 HO 119
867
81 116 126
17: 15 18:45 19:30
L3458 1721 !~236
14, 320J13, 350 13,490
1980 '860 7l"5
32. 1 28.6 "2876 "
o.oossjo.om'o.obss'o. 0069
j "~
1180 ; 1852 1178 " "7076
*"" ' '" ~~ " ' 1 i '~ " "" "
1
2,8 ...
.1-46 ..
0
:39
!
22 J26 24
3.52. :1.59 i..ai ...
0 JO .. Q . .
..-..: \
L. G. E i
22:00 , _ i _
' i
63 | ;
V99P j :
565" !
15. 2* : "" 7
"p3.pTo3*~_' " j ~.'.~~n_'
UTO"" ; " ""*"
i """
i I
312 j
2.. LQ i
270
i '
;
128 35 ' 29 "IsT" " ' " j
*Mfr's. airflow data not available for this NI, so (F/A) was calculated from exhaust composition
subsequently used with measured fuel rate to calculate air flow.
and
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 11
Date 6/24/71 Location Kellv AFB. Teat Cell 56
Engine serial No. AE-106634
Engine type T56-A15
Engine total time, hours 2779
Time (hours) since:
Hot section overhaul
Fuel
0
0
High-speed compressor overhaul
First stage nozzle guide vane overhaul
High-speed turbine overhaul N. A.
JP-4 Test Fuel
Low-speed compressor overhaul
N.A. Combustor can replacement
0
0
Low-speed turbine overhaul 0_
Additive and concentration N.A.
Inlet air humidity, Ibm H^O/lbm dry air
Relative humidity 76%
0.0167
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start Finish
79 80
29.29 29.29
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)*
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, CF
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm
NOX (wet), ppm
75% : 100% I Mil.
0:00 6:00 ... ! 11:00
2610 3838 14123
13,820, 13,800{13,820
1
1600 2085 : 21130"
33.4 33.9 '33.6
0. 0133:0. 0171 0.0180
1605 .1872 . 1.920__.
i
TakeoffFlt. Idle Accel. 'Takeoff
16:30
j
19:00
4386 J848
13,800
2275
31.4"
0. 0201
JL968....
! '
23 22 ,22
2.69 3.45 13.62
8 8 J9 "
61 93 93
7 4 6
68 97 99
21 .._
4. 04
1 1 1
102
9
Ill
13,360
930
3l7l"
07 00 8 3
1212
29
1.67
9
33
21:00
.£m&x)...,
4452
13, 820
twr^rsrp
('ma*; .
2295
31. 7
0.0201
(fflA'ty
2035 ._
21(mirt
4.04
12
111
22:00
4320
13,800
"2275""'
31.4
0.02011
1370 ._. .
21
4.04
11
102
9
111
Fit. Idle' I,. G. I.
25:00
9lT~
13_, 350
955
31.6
0.0084
1230
..
29
1,70
9.
35
2.7:00.
127
9^990.
585
i3".~4~"~
0. 0121
H. G. I.
28:3D_
233___
13, 3J50
______
130.2
'O. 0069
1,238. .
378
Li24_....
40
2_, 44__ J_._4(K
385 J18
9' " "; "
19 T"~
28 |29
*Mfr's. airflow data not available
and measured fuel rate.
y
\
F5
-------
Date 6/24/71 Location
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 12
Kelly AFB, Test Cell 56
T56-A7KB
Engine serial No. AE-104215 Engine total time, hours 5743
Time (hours) since:
Hot section overhaul 0 Low-soeed compressor overhaul 0
High-speed compressor o^
First stage nozzle guide v
High-speed turbine overha
Fuel JP-4 Test Fuel A
Inlet air humidity, Ibm HJO/lbm c
Relative humidity 43%
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO£ (wet), ppm
NOX (wet), ppm
irerhaul N. A. Combustor can replacement 0
ane overhaul 0 Low -speed turbine overhaul 0
LU! N. A.
dditive and concentration N. A.
iry air 0.0147 Start Finish
Inlet air temperature, °F 90 90
Atmospheric pressure, in Hg 29. 14 29. 14
75% ; 100% i Mil. iFlt. Idle Accel. Fit. Idle H. G. I. L.C.I.- '
0:00. 5:30.. J.l.QiQQ.. [16:.15 |17:30 19:00 ,19:45 .22:0.0 .. ;
2105 2982 '3268 ~[s40 J3470* '840 T4~23 141
13, 810J 13, 780! 13, 800113, 240 14.200 13, 240 113, 340 \9, 890
' ' ' H " " i * 1 ' """ f**O)O ' - f - j- - - -- -; -
t f \ \ '
1410 1740 1850 J895 "\ZQ52* 895 ~!765"~' 58~5 ! '
30.1 30.1 J30.1 ;27. 8 '31.8 27.8 -28.3 15.6*
0.0130 0.0161.0. 0170:0.0089 0.017910. 0089 JO. 0075 J0..0108* ..J
i ' j
: - - -J * ^WMN X ) i
1508 ^1710 1775 ^1204 1952 ;1208 :1108 J1202 :
1 ; ''
F ! i :
41 37 33 J34 i31(min^33 32 311
2.38 2.93 |3..16 U-71 j3. 46^1. 73 jl.43 2,19. __.._. ^
0 ... . 0 .JO ;0 lo 0 ._ . [0_ 228 _.
66 98 j 108 i 11 :
7 7 .5 ! ! 1 18
73 105 |113 ,35 113(^,35 "28 "":29~" ""
*Mfr's. airflow data not available at this Ni, so (F/A) was calculated from exhaust composition and
subsequently used with measured fuel rate to calculate airflow.
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 13
Date 6/24/71 Location Kellv AFB. Test Cell 56
Engine serial No. AE-103202
Engine type T56-A7B
Engine total time, hours
4879
Time (hours) since:
Hot section overhaul
0
Fuel
Low-speed compressor overhaul
High-speed compressor overhaul N. A. Combustor can replacement
First stage nozzle guide vane overhaul
High-speed turbine overhaul N. A.
JP-4 Test Fuel
0
Low-speed turbine overhaul £_
Additive and concentration
N.A.
Inlet air humidity, Ibm H2O/lbm dry air
Relative humidity 48%
0.0153
Inlet air temperature, ° F
Atmospheric pressure, in Hg
Start Finish
82 81
29. 12 29.12
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N->
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas jxres sure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm
NOX (wet), ppm
75% : 100% | Mil.
0:00 .4:30 .|9:.5Q
; i
2281 13202 i 3465
13,790j 13,800J 13,800
i
1
1465 : 1820 i 1950
30.7 ,30. 7 1 30. 7"
0. 0"l33'0. 0165 6. 0176
1 50.5 ...1710 _., 1780__.
!
Fit. Idle! Accel.
15:30 [17:00
i
504
'13,240
3710
14,250
790 12070
28.3 !32". 7
6. 0077 "670176
a IPO
'
49 38 ... i 32
2.53 .3.11 13,31
o.. .0 ;p
78 109 :118
998
87 us ;i26
36
|1,.51
4
I
32
19QO
31 .
3.45
o
117
Fit. Idle
18:45
H. G. L
20:30.
442 !274
13, 250_
770
13, 330
"715"~
28. 3 28. 5
0. 0076 6. 0070
1082 1040
35 . _,
1.43
A
~
23
7
30
L. G. I. i
21;30 .j
79
9^920
555 " '
15. 3*
o.'oioi*
1124
i !
35 J279 |
L34... 12.04 j
4 232 '
13 ' ;
j 17
27 30 ;
#Mfr's. airflow data not available at this Nj, so (F/A) was calculated from exhaust composition
subsequently used with measured fuel rate to calculate airflow.
and
-------
APPENDIX B
Data on Emissions from J-79
Turbojet Engines
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 14
Date 1/1/71 Location Kelly AFB. Test Cell 48
Engine type J79-GE-15
Engine serial No. GE 418312
Engine total time, hours 1492
Time (hours) since:
Hot section overhaul
o_
.0 Low-speed compressor overhaul _
High-speed compressor overhaul N. A. Combustor can replacement
0
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul N. A.
JP-4 Test Fuel
0
Low-speed turbine overhaul 0_
Additive and concentration N. A.
Inlet air humidity, Ibm H-O/lbm dry air
Relative humidity 52%
0.0176
Inlet air
temperature,
Op
Start
89
Finish
89
Atmospheric pressure, in Hg 29. 34 29. 34
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N,
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, ° F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NOg (wet), ppm **
NOX (wet), ppm
Idle Mil.
0:00 ;7:15
26.0 __. 10,0.80
5030 ,7690
,
1200 :8850
46.3* 163.4
OYOO 72*6. 0150
666 1165
317
1.45
112
4
6
10
100% i 75% Jdle
I.9:0fi j 29:00 40:30 ,
.9.^150...! 6^140 ..J.29J) ...J.
7360 J6830 5015 ! I
8100 J5200 11150 i
156.6 1125. 5 144.4* '
6". 61441 6 .011 5 1 0 TOO? 2*
t i . j
i i '
; i !
- t ' -j '--
1142 J949 ,680 j
i 300 !
i .1.45..!
80 i !
;... ;... =8 .. : !./"
4
!12
., ,
. J ... _-
|
j 4
1 i
i !
i
- -.-. - ^ -. 1
*Airflow data not available for Nj < 6000, so (F/A) was calculated from exhaust composition and
subsequently used with measured fuel flow to obtain airflow.
**By subtraction.
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 15
Date 7/1/71 Location Kelly AFB, Test Cell 48
Engine total time, hours 1492
Engine serial No. GE 434176
Time (hours) since:
Hot section overhaul 0 L Low-speed compressor overhaul
High-speed compressor overhaul N* A. Combustor can replacement
Engine type J79-GE-15
0
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul N. A.
JP-4 Test Fuel
Low-speed turbine overhaul 0_
Additive and concentration N. A.
Inlet air humidity, Ibm H2O/lbm dry air 0.0159
Relative humidity 53%
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start. Finish
88 87
29.26 29.26
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, ° F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm#*
NOv (wet), ppm
Idle
0:00
275
5060
1275
48. 5
! 75%
.16:25 _
6650
16910
5775
* 129.7
0. 0073*0.0124
675 960
402,
1.48
27 5 G
8
3
11
44
2.33
39
4
43
i 100%
i ?_7: 15
19500
1
i
17400
i ~ '
8350
: 1 56.4"
0. 0148
:il35
c
,29
-.2.7.5...
:o ..__.
6
68
! Mil.
S?7:45 .
[10, 100
1
j7660
i8875
'.162. 1
|0.0152
1156
i
J23
1.2 ,.7.7
,7Q....
7
77
! Idle
;47:40
J300
1
1 a, ,
J5060
i43. 7*
! ; !
i
i
-
1
.
10.0070*
>640
j "
Jl, 41 ..
160. .
|H
14
il5
.. _
-- -r
i ! ;
- , . r . .
. .
j ;
:
*Airflow data not available for Nj <6000, so (F/A) was calculated from exhaust composition
subsequently used with measured fuel flow to obtain airflow.
and
IP
i
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 16
Date 7/2/71 Location Kelly AFB, Test Cell 48
Engine serial No. GE-E418975
Engine type J79-GE-15
Engine total time, hours 2075
Time (hours) since:
Hot section overhaul
0
_0 Low-speed compressor overhaul
High-speed compressor overhaul N.A. Combustor can replacement
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul N.A.
JP-4 Test Fuel
Low-speed turbine overhaul p_
Additive and concentration N. A.
Inlet air humidity, Ibm HJO/lbm dry air 0. 0153
Relative humidity 43%
Inlet air temperature, ° F
Atmospheric pressure, in Hg
Start Finish
91 89
29.26 29. 26
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N,
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NOg (wet), ppm**
NOX (wet), ppm
Idle i Mil. i 100% 1 75%
0:00 . 11:0.5.. j 20:15. [30:0.0
320 10,0001 9,200 !6A150
! 1
i 1 ,
5050 j 7685 i 7380 16910
1200 8775 18000 '5150
43. 8* 161. 5 ; 153.9 ; 128. 1
0. 0076*0.0151 0.0144:0.0112
i
665 1157 1130 ;:909
t" -
i
371 23 !43 J38 .
1.33 2.85 :2..6.8 :.2.J9
124 1 1 .... 0
7 71 56 .32
4 5 5 4
11 76 61 36
Idle
.39:30
340
506~0 j
" """' 1
1180 ;
43. 7*
0. 0075*
f
649 ;
305
1.51 H
62
7.
3
10
j
i
-
!
1
i
1
i
i
i
1 J
i
...... . _. ^
*Airflow data not available for NI <6000, so (F/A) was calculated from exhaust composition
and subsequently used with measured fuel flow to obtain airflow.
**By subtraction.
CP
i
-------
Date 7/6/71
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 17
Location Kelly AFB, Test Cell 48 Engine type J79-GE-15
Engine serial No. GE 418312
Engine total time, hours 2149
Time (hours) since:
Hot section overhaul
Fuel
High-speed compressor overhaul
First stage nozzle guide vane overhaul
High-speed turbine overhaul N. A.
JP-4 Test Fuel
Low-speed compressor overhaul 0
N.A. .Combustor can replacement 0
0
Low-speed turbine overhaul 0_
Additive and concentration N. A.
Inlet air humidity, Ibm H,O/lbm dry air 0. 0167
Relative humidity 66%
Inlet air temperature, ° F
Start
80
Finish
83
iniet air temperature, x ou BJ
Atmospheric pressure, in Hg 29. 35 29. 35
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N,
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, ° F
Exhaust gas temperature, ° F
Exhaust gas pressure, jpsia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO^ (wet), ppm**
NOV (wet), ppm
Idle 'Mil, ' 100% ' 75% ' Idle Mil. Idle j
0:00 17:0.0 i.34:.Q0 j44:.QO 52:00 54:00 62:30, ] !
230 10,25019, 620 6,310 [230 10,200245 j
: i 1 ' : ! ;
4965 !7665 i7380 16880 15000 7665 5000 |
j . ;
1175 8850 18200 5300 ll'lTO 8850" [1175"} " '
45.9* 163.6 il57.8 130.3 !43. 9* 163.6 41.8* |
0. 0071*0. 015270. 0144 ;0. 0113 i6. 0074*0. 0152 0. 0078^ " ~ :
r
'. - -i . ,-i ,' ,.i_ _ . ..... ...... t -- IT--- - -
654 1158 -1135 924 |652 1160 1654 i
: ! ! i
385 13 :29 43 352 13 351 :
1.43 2.96 i2..78. ...2. 3.7 jl.50.J2. 88 1, 5.8. . _ _ ,..'
145 0 |1 __1 1.12... 0 |105_
4 71 '58 32 4 :?4 14 "
5 6 6 5 16 8 |6 !
9 77 64 37 ilO 82 10 i '
*Airflow data not available for Nj <6000, so (F/A) was calculated from exhaust composition and
subsequently used with measured fuel flow to obtain airflow.
** By subtraction.
CP
i
-------
APPENDIX C
Data on Emissions from Commercial
Turbojet and Turbofan Engines:
CJ-805; JT3C-6; JT3D-3B
JT4A-11; JT8D-1 & 7; JT8D-9
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. is
Date 7/12/71 Location TWA Overhaul Facility,
Tell 5
6144
Engine type JT8D-9
Engine serial No. P665244R (TWA 3q20) Engine total time, hours
Time (hours) since:
Hot section overhaul 6144 Low-speed compressor overhaul
High-speed compressor overhaul 6144 Combustor can replacement
6144
First stage nozzle guide vane overhaul 6144
High-speed turbine overhaul 6144
Fuel JP-4 Test Fuel
0 (674344-674345)
Low-speed turbine overhaul 6144 ._
Additive and concentration N.A.
Inlet air humidity, Ibm H^O/lbm dry air 0. 0171
Relative humidity 72%
Inlet air temperature, ° F
Atmospheric pressure, in Hg
Start Finish
80 80
28.81 28. 81
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, ^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, ° F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm***
NOV (wet), ppm
Cruise METO^Takeoff
1:00 15:10
9,420 ll", 900
7220 7740
11, 100 11,460
5400 6960
114.6 ; 132.5
Idle
26:30 31:00
13,l>9bi996
8120
11,630
8210
145.7
0. 0131 0. 0146 0. 0157
1.652 1.864
2.035
912 992
9.0 12.0
11 14
2.32 2.75
3 : 2
61 94
3 " "5~" """
64 99
1065
14.4
12
3.05
"l
124
8
132
4980
7110
1230
- -
i !
i i
:
; | ;
i . . i , . .
! ! :
43. 2*^ ^
0. 0079**
L j
1 j
i i
[ ~i -|
i
, .. 1~ . i . _ . j
1 j ! i
' . .. _l 1 1 !
694
0.6
161 !
1.67 ! !
"so- ^ -| i
3 : '
'5~ " i" " i
8 i :
i
; i
1 '
i
I i -
| s
!
1 ' '
j- j - i
*Maximum Except Take Off.
**(F/A) and airflow calculated from exhaust composition.
###By subtraction.
C>
l
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 19
Date 7/13/71 Location TWA Overhaul Facility, Test Cell 5
Engine serial No. T631329B (TWA 2060) Engine total time, hours 24.419
Time (hours) since:
Hot section overhaul 9130 Low-speed compressor overhaul 9130
Engine type JT3C-6
Fuel
High-speed compressor overhaul 9130 Combustor can replacement 9130 (224-0680) 8 ea.
First stage nozzle guide vane overhaul 9130 Low-speed turbine overhaul 9130
High-speed turbine overhaul 9130
JP-4 Test Fuel
Additive and concentration
N. A.
Inlet air humidity, Ibm H-O/lbm dry air Q^ 0191
Relative humidity 73%
Inlet air temperature, ° F
Atmospheric pressure, in Hg
Start
85
28.91
Finish
83
28.91
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, No
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
COz (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO^ (wet), ppm **
NOX (wet), ppm
Idle 'Reverse Idle iCruise METO Takeoff Idle i i !
1:00 . ;4:45_.._
360 8220
2105 J6bi6~~"
5780 ;934d~
980 J6860 "
36.3* 152.9
6 L.30 .
440
2260 _J
6020
990
37.2*
0. 0075*0. 0125 0. 0074*
1. 10 2. 20 ;1...10__.
580 993 ^555
0.4 16.4
0.4
785. 33 ... .694
1.26 2.35 jl.26. ..
1730 16 ,1.5 5P~-
2 51 jl
5 4
7 55
;6
|7
15:00 :18:00 ,22:30 , 27:00....!. ,_ ! _.
6480 7140 9500 560
. _i_ r._ _f. .._.__. ._. __
- - - - 1 - 1 - - i
5710 15830 16300 [2115 j !
9110 +9170 9620 "16420 !
5400 |6070 i8050 1210 i i i
,140.1 J145. 8 ,163.3 43.7*1 | ] _
0. 0107 0. 0116 b". 0137 JO. 0077*! ,----
- . ) | . .- 4 , .,. . - , .. __, .
L53 2_._Q4. J2, 4_0_ _j_L_.U_ ] _. .t J
j... i ... i . . J .
870 937 1085 502 i j '
12.6 14.1 19,5 0.6 ': ' i
45 ?.ft A4n | i ! '
2..IO J2. 3.1 2.6.6 1.37... | ! _.'\
17. ,11 ill ..... .. 1020.. 1 ! ;
3.3 _ . 43 . ._[?! ..... U . ! I \
9 6 :3 6 ;
42 ^9 |74 ' 7. ! ;
*(F/A) and airflow calculated from exhaust composition.
**By subtraction.
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 20
Date 7/13/71 Location TWA Overhaul Facility. Test Cell 5
Engine type JT8D-9
Engine serial No. P674299B(TWA 5422) Engine total time, hours 3674
Time (hours) since:
Hot section overhaul 0 Low-speed compressor overhaul
High-speed compressor overhaul 3674 Combustor can replacement
3674
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul 3674
JP-4 Test Fuel
0
Low-speed turbine overhaul 3674
Additive and concentration N. A.
Inlet air humidity, Ibm H JO/lbm dry air 1.0152
Relative humidity 68%
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start
79
28.92
Finish
79
28.92
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gasj>ressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO^ (wet), ppm*
NOX (wet), ppm
Cruise ! METO
0:00 5;00 _j
9,450 11^320
7160 7~550
10.83Q 11, 160
5470 6520
115. 1 I 128. 5 ~
OT32 "d."0141
1.65 1.81
Takeoff Idle !
11:30
13,400
_16:3_0
L020
" J " "1
8060
11,480
7950
.
2850 j_
7,120
1190 1
144. 1 i 34. 1
6; Of 53; 0.0097
2.02
i '
895 941 | 1009
9.1 11.3
26 20
2. 65 . 2. 80
1 0
63 85
6 4
69 89
14. 1
17
3.05
0
120
8
128
681
Po.6
305..
1.85
94
2
8
10
-
-
i
i !
!
" | 'T- '
, j 1
"_-_rr7~ ^ n. ""!_:
1 ; ! i
. _ _,
i
-j --T
j
i
1
I '
j '
*By subtraction.
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 21
7/14/71 Location TWA Overhaul Facility, Test Cell 5
Engine type JT8D-9
5839
Engine serial No. P665338B(TWA 3944) Engine total time, hours
Time (hours) since:
Hot section overhaul 3343 _ Low -speed compressor overhaul _
High-speed compressor overhaul 5839 _ Combustor can replacement 0 (674344-674345)
First stage nozzle guide vane overhaul 3343 _ Low-speed turbine overhaul 5839 _
5839
Fuel
High-speed turbine overhaul 5839
JP-4 Test Fuel Additive and concentration
N.A.
Inlet air humidity, Ibm H -O/lbm dry air
Relative humidity 74%
0.0131
Start
Finish
75
Inlet air temperature, °F 70
Atmospheric pressure, in Hg 28. 92 28. 92
Mode
Cruise iMETO I Takeoff Idle Reverse
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
0:00 .. 11 :.P_Q ,26jOQ_J.31 :.30_ j 38:30
9,350 rii
7110 J 7520 __
10,830;il~ 240
13,740
840
8090 12610
11,
5350
7940
_630;6870 I1.L.590
j 6520_ [825(3... 1101Q.. J780Q.
11JL-.0._ 12?..3 _[L47_._4 [3_5. 5* 144.JL
0 ..01.29. P. 0134; 0. 0156 fb~. 0079^0. 0150
1.64 1.82 12.04 i
9:
1017 !659
;14. 8~ foTs"
1012
14.2
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm **
NOX (wet), ppm
6 12 i9 - .126.0...
1.99 12. 13. |2....38_....U-5^
1 .. |p JO. [8Q
63 85 _ |12.1 ;3
6 6 " '" 1 ;9
69 91 128 !l2
12
2.36 ..!
6
117
*(F/A) and air rate calculated from exhaust composition.
**By subtraction.
O
i
0\
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 22
Date 7/15/71 Location TWA Overhaul Facility. Test Cell 5
Engine type JT8D-1
Engine serial No.649L37B (TWA 2840)
Time (hours) since:
Hot section overhaul 2789
Engine total time, hours 8574
8574
Fuel
High-speed compressor overhaul
First stage nozzle guide vane overhaul
High-speed turbine overhaul 8574
JP-4 Test Fuel
Low-speed compressor overhaul
8574 Combustor can replacement
2789
2789
Low-speed turbine overhaul 8574
Additive and concentration N. A.
Inlet air humidity, Ibm H2O/lbm dry air 0.0143
Relative humidity 82%
Inlet air temperature,
Atmospheric pressure
°F
, inHg
Start Finish
72 72
28. 87 28. 87
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N,
Engine speed, N?
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm **
NOV (wet), ppm
Cruise METO
0:00 4:00
9,600 11,330
:
7270 J7680
11, 140- 1 1,470
5530 '6620
Ui.2..l2.7^7__
0.0133.0.0144
1.65 1.80
852 915
9.1 11.2
32 15
2.63 '2.72
4 '4
50 63
6 4
56 :67
Takeoff
.7:30
13,040
8080
11,750
77.60...
J,4Q.._1_
0.0154
1.94
990
13.3
6
2.98
5
,81
3
;84
Idle
J2:30
680 _j
2550
6620
950
2.6, 4*
0.0100!
(.,. -
687
0.4
474
1.95
152
'3'"
8
11
Reverse
14:50
13,040
8100
fl, 780
7810
14a,.l
=0.015.5
1.J90
990
13.3
22
3.19...
10
80
7
87
_
t i
1
1 "' " " -" \
i
i
|" -- - -*-
i n
]
I
: 1 *
1
1
'
*(A/F)and air rate calculated from exhaust composition
*#By subtraction.
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 23
Date 7/15/71 Location TWA Overhaul Facility. Test Cell 5
Engine serial No. 631329B
Engine type .TT3C-6
Engine total time, hours 24. 419
Time (hours) since:
Hot section overhaul 9130
Fuel
Low-speed compressor overhaul 9130
High-speed compressor overhaul 9130
.Combustor can replacement 9130
First stage nozzle guide vane overhaul 9130
High-speed turbine overhaul 9130
JP-4 Test Fuel
Low-speed turbine overhaul 9130
Additive and concentration N. A.
Inlet air humidity, Ibm H,O/lbm dry air 0.0147
Relative humidity 53%
Start
86
Finish
86
Inlet air temperature, ° F
Atmospheric pressure, in Hg 28. 89 28. 89
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, ° F
Exhaust gas temperature, °F
Exhaust gas jpressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm**
NOX (wet), ppm
Cruise iMETO ^
0:00 7:00
6520 7360
>
5710 i 5860
9090 ;9240
5560 -61601
139.9 146. 5
0. OHO'O. 0117
1.95 2. 06"
692 !730
12.8 14.6
39_ 8.. .
2.17 .2.38,
24 :19
43 47
0 1
43 48
Fake off
20:00
9560
Idle iReverse
25:00
360
. _
6290
9610
si "QQ__
162. 5~
o.oiTs
" 2. 44
1077 "
119.6 ^
5
2.61
.
;13
!69
il
;70
2300
5870
1120
37. 5*
0.0083s
1. 10
30:00
8400
t *
6050 1
9360 _ ;
7070 :
153.5
'0.0128
2."25~"
... ._] . _ 1
j
"537 ]l005 f~
0.5
2£8.
1.40, .
1930
3
17.0
2.1 :.
2, 49 .. .
13
57
3 1
6 J58 ;
1
'
l
;
,
'"" "1" " I"
I
1
._. , ^ _,. --
i
!
i
- 1 +-
1
1
!''- ' ' 1 ' - -
' i ;
*(F/A) and air rate calculated from exhaust composition.
**By subtraction.
P
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 24
Date 7/1 S/71 Location TWA Overhaul Facility. Test Cell 5
5923
Engine serial No.P665336B (TWA 3942) Engine total time, hours
Time (hours) since:
Hot section overhaul 0 Low-speed compressor overhaul
High-speed compressor overhaul 5923 Combustor can replacement
Engine type JT8D-9
5923
0
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul 5923
JP-4 Test Fuel
Low-speed turbine overhaul 5923
Additive and concentration N. A.
Inlet air humidity, Ibm H,O/lbm dry air 0.0123
Relative humidity 53%
Inlet air temperature, ° F
Atmospheric pressure, in Hg
Start Finish
82 80
28. 88 28.88
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
COE (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO£ (wet), ppm*
NOv (wet), ppm
*By subtraction.
Cruise METO
QjHO 15.-JUL-
9.500 11.8501
7330 "' 7730
10,930 11, 370
5600 7000"
114. 2 > 132. 1
0.0140, 0.0147
1.65 1.86
910 985
9.1 12.0
11 8
2. JJ 3 _;2.97
10 ; 10
70 ;100
5 6
75 106
Takeoff Idle f}pVprsp>
.32.; QQ-43 7-00 j 4.2:00
13.50oi920 i 12,750,
r 1 ""
i j
8120 J2750 J7900 : ,
ll, 620 7020 ,11,450
8160 1 930 17700 '
144.4 ;32.6 j 138. 7
0.0157:0. 007910. 0154:
2.01 , j
"1 ""
1046 1680 !l017 :
14.2 |0.6 [13.1
6 i 269..... j.7-
3,.15_ ;.L61 J3. 1.0... i.
10 ^80 !14
L125' is ;108
6 ,7 ;~5
131 12 J113 1
- - f
1
i ------ i ... . . .. - ..
f
i
i
- - - '
j :
' i
. .. .. i !
i !
i ,
: j
p
1
O3
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 25
Date 7/16/71 Location TWA Overhaul Facility, .T_est_C^11_5 Engine type JT8D-9
Engine serial No. P665244B (TWA 3920) Engine total time, hours 6144
Time (hours) since:
Hot section overhaul 6144 Low-speed compressor overhaul 6144
High-speed compressor overhaul 6144 Combustor can replacement 0 (674344-674345)
First stage nozzle guide vane overhaul 6144 Low-speed turbine overhaul 6144
Fuel
High-speed turbine overhaul 6144
JP-4 Test Fuel
Additive and concentration
N.A.
Inlet air humidity, Ibm H2O/lbm dry air 0.0133
Relative humidity 56%
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start Finish
80 82
28.94 28.94
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, J?sia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm**
NOX (wet), ppm
Cruisp 'METOJTakeoff
0:00 ' 3:00
9, 580 ; li",340
7200 " 1 7580"
10"/810? fr, 160
5680 S6640"
116. 1 i 129.0
y_:QO.
13, 540
Idle Reverse
.19:00.
760
r - -] - -i
8110
IT, 550
8190
145.6
31:00
JLL.MQ
i
2570 L8120 i
6630 " Tl, 580;
880 1 8350
28.8* 14670
0 . Q 1 3.6: 0 ..0143: 0 , OJ 5 7 0 .. 0.0 8 #0 . 0 1 5.9
905 966
9.1 11.2
.13. 1.4
2. 38 2. 42
0 ,0
70 89
4 4
74 93
' 1070"
14.2
, 1.2
0
'' 1 20
.7
127
"69'l "
1053
0.5 |14.3
333..
1.1.67
'3
9
12
A3. .
2.69
0
122 "
,5
|127
.
_
...
. ._ .
i
!
-- - - - i
1
i j
i
j
I
j
i
i
v t
i :
*(F/A) and air rate calculated from exhaust composition.
**By subtraction.
P
i
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 26
Engine type JT4A-11
7/16/71 Location TWA Overhaul Facility. Test Cell 5
Engine serial No. TWA 2233 Engine total time, hours 26.795
Time (hours) since:
Hot section overhaul
2993
13,286
Fuel
. Low-speed compressor overhaul
High-speed compressor overhaul 13,286 Combust or can replacement 2993 (22-0533)
First stage nozzle guide vane overhaul 13» 28^ Low-speed turbine overhaul 13,286
High-speed turbine overhaul *3, 286
JP-4 Test Fuel Additive and concentration
N A.
Inlet air humidity, Ibm H JO/lbm dry air 0.0153
Relative humidity 50%
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start Finish
89 89
28.87 28. 87
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N?
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm **
NOX (wet), ppm
Cruise METO
0:00 5:00__H
10,020 12.28Q
5785 76140
8440 8730
8580 10,670
205. 2 220/8
0.0116. 0.0134
977 1107
13.7 17.2
22 19
2.43 2.76
1 0
54 75
3 2
57 77
Take of fl Idle
,10:00_ 13:00
"13,760 580
6450 2115
8930 5250
12,200 1360
"2 3 176" "5 9.0*
0. 0147 0.0064*
1194 623
18.9 JO. 6
:17 j453 '
;2. 82 '1.25
'0 T800
95 " 3
2 5
97 8
Reverse
17:00
12,600
6130 i |
8750 1
n,no;
220.2 "
0.0140;
, .
i i
.
1121
17.9 i
16 !
2. 69 . I
2
76 ' \
2 i
78
i
: j
- i
i
i
i '
!'
1
1 ;
i
: |
'
i
[
i (
i , j
! i
;
r , n J - ': ,, , .
i
; i
i
r -'..-- - ;
*(F/A)and air rate calculated from exhaust composition.
**By subtraction.
P
i
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 27
Date 7/19/71 Location TWA Overhaul Facility. Test Cell 5
Engine total time, hours 15. 372
Engine type JT3D-3B
Engine serial No. TWA No. 2304
Time (hours) since:
Hot section overhaul 74 Low-speed compressor overhaul 15, 372
High-speed compressor overhaul 15, 372 Combustor can replacement 74
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul *5, 372
JP-4 Test Fuel
, 372
Low-speed turbine overhaul 15,372
Additive and concentration N.A.
Inlet air humidity, Ibm H^O/lbm dry air 0.0107
Relative humidity 75%
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start
_63
28.9
Finish
64
28.95
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO^ (wet), ppm**
NOX (wet), ppm
fr-nico METO
0:00 ; 10:00..
11,060 13,200
5785 ;6180
9220 '9660
6170 !7590
6~dl23~0.of37
1.50 1.65
761 825
6.4 8.5
26 20
1.60 2.04
52 65
27 44
5 6
32 50
Takeofl
25:00
15,400
-
6510
9850
9190
0.0149
i 1. 82
914
!10.8
14
1.2.51..
: 68 . _
71
4
!75
Idle ,
3.3:00
1060
3710
62~20
1070
.38,6*
6.0077*
i .
504
0.3
1658
U..3.9 ..
1060
0
;7
7
Reverse
40:00
15,400
6510
9 8 20" "
9230
171. 5
0.0150
1
r
917
10.6
.U.. .... _
2.44
70
70
;75
-~
j
"
, .. ...
"* °
...... ...
-
...
*(F/A) and airflow calculated from exhaust composition.
**By subtraction.
-------
AIRCRAFT EMISSIONS BASELINE DATA -TEST No. 28
Date 7/19/71 Location TWA Overhaul Facility, Test Cell 5
Engine serial No. TWA No. 3102
Time (hours) since:
Hot section overhaul 9463
Engine total time, hours 9463
Engine type JT3D-3B
Low-speed compressor overhaul 9463
High-speed compressor overhaul 9463
.Combustor can replacement 9463
First stage nozzle guide vane overhaul 9463
High-speed turbine overhaul 9463
Fuel JP-4 Test Fuel
Low-speed turbine overhaul 9463
Additive and concentration N. A.
Inlet air humidity, Ibm H-O/lbm dry air 0.0101
Relative humidity 46%
Inlet air temperature, ° F
Atmospheric pressure, in Hg
Start
75
28.97
Finish
75
28.96
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO^ (wet), ppm**
NOV (wet), ppm
U7 EPBiCruiselMETO takeoff 1 Idle Reversd- I 1
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No.
Date 7/iq/71 Location TWA Overhaul Facility. Test Cell 5
Engine serial No.6ll089 (TWA 2221)
Time (hours) since:
Hot section overhaul 10,505
Engine type .TT4A-11
Engine total time, hours 22 ,911
10,505
Low-speed compressor overhaul
10,505 Combustor can replacement 10. 505 ( 394323)
First stage nozzle guide vane overhaul 10» 505 Low-speed turbine overhaul 10» 505
High-speed compressor overhaul
Fuel
High-speed turbine overhaul 10,505
JP-4 Test Fuel Additive and concentration
N.A.
Inlet air humidity, Ibm H^O/lbm dry air
Relative humidity 50%
0.0093
Inlet air temperature, ° F
Atmospheric pressure, in Hg
Start Finish
73 73
28.97 28.98
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas jpres sure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
N©2 (wet), ppm**
NOX (wet), ppm
Cruise METO Takeoff
Idle Reverse
0:00 11 : 00 j 21 : OJ) j 24 : 00
9,980 12,100 1 14,460 660
I
' \
5670 j6020 J6520
8310 '8630 J9000~
8,280 10,350;12,860
206.8 ;223.0 1238.8
0.0111 0.0129 0.0150
905 1040 ! 1201
13.9 17.2 120.8
2240
"54 ib
1,250
54.3*
0.0064*
i_ _.
498
,0.7
29_._ 25 .. ,25 ._ |384 _
2.18 2.53 '2,94 ;i_, l_i
1 0 ?0 i735
47 65 195 ~ 2
5 5 ,5
52 70 ;100
,6
8
30:30
13^.240 i
; i
i | i
' i
6220 [
8750
1 17400
230.6
0.0137 ;
. | L
1108 1
18.9 !
,33
2,71....
0
76
5
81
__. . . .
j :
', |
i
I
' -f-
j
" '~T '
j
" I"" "
|
1
, !
- - i
1 I
I -. ,
O
*(F/A) and air rate calculated from exhaust composition.
**By subtraction.
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 30
Date 7/20/71 Location TWA Overhaul Facility, Test Cell 5
Engine 8erial No. GE-161-302 (TWA 274%ngine total time, hours 19,618
Time (hours) since:
Hot section overhaul ° Low-speed compressor overhaul
Engine type CJ-805
High-speed compressor overhaul N. A.
First stage nozzle guide vane overhaul _
High-speed turbine overhaul N. A.
Fuel JP-4 Test Fuel
0
.Combustor can replacement 0 (23-0410)
Low-speed turbine overhaul 0
Additive and concentration
Inlet air humidity, Ibm H~O/lbm dry air 0.0111
Relative humidity 56%
Inlet air
temperature,
°F
Start
74
Finish
75
Atmospheric pressure, in Hg 2Q. 04 29. 04
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N^
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, j>sia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm**
NOV (wet), ppm
Cruise METO JTakeoff i
0:00 5:00_.
7720 8620
i
7080 ,7180
6390 i 7220"
145. 0; 152.8
0,01 22 ! 0.0131
2.10 2.24
957 T024
15.6 17.7
57... 48
2.51 2. 70
2 0
53 62
6 7
59 69
Idle i ' ;
10:00 113:00
9620 J400
' 't
J
7280
8140
: 1 567s
j
.0,0145.
' £t _ ~jt J.
! 1100
:20. 1
4-5
:0
^74
\ 8
:82
4490
;. -. .
i [ 1 : . i _
1090 ]
36. 0* ' "~
0.0084* ;
_ . . 1 . . . '
727
17). 4
464 ..
-A, 63
302
1
'a
9
j i ' - 1 ------
1
_.. J
. _
i . |.. . . .
i j
j !
i
- .. i
;
1
i -
i
i l
t 1
1 ~| "
_ ., f
._. . 1
1
i
1 i
- ( ' "
j
1
... i
- ...- i __ .... ;
; i
P
*(F/A) and air rate calculated from exhaust composition.
**By subtraction.
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 31
Date 7/20/71 Location TWA Overhaul Facility. Test O.11 5
Engine serial No.GE-161-302 (TWA2743) Engine total time, hours 19,618
Time (hours) since:
Hot section overhaul_2 Low-speed compressor overhaul
High-speed compressor overhaul N. A. Combustor can replacement
First stage nozzle guide vane overhaul 0
High-speed turbine overhaul N. A.
Fuel JP-4 Test Fuel Additive and concentration
Engine type CJ-805
Low-speed turbine overhaul °_
N. A.
Inlet air humidity, Ibm H _O/lbm dry air 0. 01Z1
Relative humidity 51%
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start Finish
76 80
29.03 29.02
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NOjj (wet), ppm**
NOX (wet), ppm
~ruise ! MET O takeoff
0:0.0 5:00 j 8j50
7720 8660 ! 9800
i
7100 17210 17350
"- ' -j -' ~
i
6390 ; 7480 ! 8370
144.9 153.0 j 160.1
0.0122. 0.0136 0.0145
959 1045 ^1126
15.5 17.7 '20.2
52 43 ... i 43
2.34 2.62 :.2..91. .
4 0 '0
52 64 81
576
57 71 ^87
Idle
13:00
380
4490
1080"
38.0*
0.0079s
734
ro;"4 "
,3.97 .
.1.52
353
1
7
8
, i
'
i --j-
--- i ]
'
>"~ : ' 1 ......
1. .. _
i
|
i
... i
j
j.
: 1
' - i --- -
1
i
1
:'" ~~T
i
i
1
! i
i
1
I
1 . .
]
*(F/A) and airflow calculated from exhaust composition.
**By subtraction.
P
i
in
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 3Z
Date 7/21/71 Location TWA Overhaul Facility, Test Cell 5
Engine serial No. P654564B(TWA 3702) Engine total time, hours _8706
Time (hours) since:
Hot section overhaul _0 Low-speed compressor overhaul
High-speed compressor overhaul 8706 Combustor can replacement
Engine type JT8D-7
8706
0
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul 0
JP-4 Test fuel
0
Additive and concentration
Low-speed turbine overhaul
N. A.
Inlet air humidity, Ibm H-O/lbm dry air 0.0121
Relative humidity 58%
Start
Finish
70
Inlet air temperature, ° F 72 ,v
Atmospheric pressure, in Hg 28. 98 28. 9.7
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gasj>ressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm *
NOX (wet), ppm
Cruise! METOJTakeoftf Idle
0:00 4:30 111:00 '20:30
9,600 : 11, 360 ! 13, 000 il, 040
j 1
7210 ;7610 18000 J4140
10, 930 1 1, 2lO~"i 1 1, 490 ~7~"~2~80~"
5550 6620 J7720 '1020
112.5 125.0 J136.5 J36. 5
0. 0137" 0. 0147'"0. 0157 ;0".0080
1.64 1.79 ;1.94 j
902 960 11020 |696
9.2 11.2 i!3.2 [0.7
21 17 13 1302
2.72 2.93 ;3.12 1.61
1 0 !0 140
83 104 121 4
6629
89 110 123 13
j :
,- . - . i.
' ~ ~
. "f" " ' "
_. - .
: . .. _j._
1
' - j- -
: 1
i . i
i
i
i
i
i
:
... _i
i
i
j ,,
1 - - -
_... ,
t ~~ "
-
n
*By subtraction
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No.
Date 7/Z1/71 Location TWA Overhaul Facility, Test Cell 5
Engine serial No. 161-255 (TWA 2688)
Time (hours) since:
Hot section overhaul 0
Engine type CJ-805
Engine total time, hours 21, 747
Low-speed compressor overhaul 0_
High-speed compressor overhaul N. A.
First stage nozzle guide vane overhaul
High-speed turbine overhaul N. A.
Fuel JP-4 Test Fuel
0
.Combustor can replacement 0 (323-0410 - 323-0411)
Low-speed turbine overhaul 0
Additive and concentration N. A.
Inlet air humidity, Ibm H2O/lbm dry air 0.0119
Relative humidity 58%
Inlet air temperature, ° F
Atmospheric pressure, in Hg
Start Finish
75 75
28.93 28.94
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pjressure, psia
CO (wet), ppm
COZ (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm**
NOX (wet), ppm
Cruise iMETO ^Takeoff! Idle
0:00 5:55 , 12:00 [ 15:45
8220 " 8560" I 99 40~ ! 400
7115 ^7165 7330 1 4530
- - r j ~
6550 i 6910 '_; 8350 j 1060
147. 7 : 150.8 [161. 1 j 36.4*
6". 0 1 23~ 0 . 0 12T 6To 1 44 1 0 .0081
2.16 2.24 2.46 !
.
977 "1002 i 1127 729
16. 5 17. 5 20.8 ! 0.4
52 44 ; 38 j 552
2.54 .2.59 12.90 il.56
0 0 1 0 J488
54 59 i 77 "2
6 5 |6 6
60 64 : 83 j 8
... _. . .r__ _. 1
i
"p
.
* ~ "~" ; ;
t
I :
'
i
!
l
i
i
L.
' i
. J
. ^ "~; '
- -- t --
1 '" '" ' t ' ' -
f
- - -. .
*(F/A) and airflow calculated from exhaust composition.
O
i
-------
AIRCRAFT EMISSIONS BASELINE DATA -TEST No.
Date 7/22/71 Location TWA Overhaul Facility, Test Cell 5
Engine type JT4A-11
Engine serial No. P611135B (TWA2237) Engine total time, hours 27,483
Time (hours) since:
Hot section overhaul 284 Low-speed compressor overhaul 8050
High-speed compressor overhaul 8050 Combustor can replacement 284 (222-0533. -0534, -0536)
First stage nozzle guide vane overhaul 284 Low-speed turbine overhaul 8050 ._
Fuel
High-speed turbine overhaul 8050
JP-4 Test Fuel Additive and concentration
N. A.
Inlet air humidity, Ibm H JO/lbm dry air
Relative humidity 73%
0. 0146
Start
76
Finish
78
Inlet air temperature, °F
Atmospheric pressure, in Hg 28. 9.1 28. 9_1
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gasj>ressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm **
NOX (wet), ppm
Cruise ;METO !
0:00 6:30. . ,
5660 i 5950
8400 ,8650
8,040 :. 9,480
203 218
0. Ollb" 0.0121
2.04 2.25
934 1037
14.0 16.7
27 22 _
2. .18 2.49
4 1
49 61
2 3
51 64
Take of fl Idle Reverse i : ;
10:50 } J6:00 18:00
14,1801520 114,200
! ! 1 :
6430 i 2020 j 6420 i ! {
9030 5100 '9010 1 t
12,00.0! 1,260 j 12,040 j
235 J52* J234 . " "" "" " ~ "" ' T
0.0142I0.0068*J 0.0143 ' "'
2.56' i "" ] : " "T~"
! ' ;
.1202 ;547 ,1204 " '""~~~"
, 20.5 JO. 5 J20.5 '
.17 1473 . ..jil j
i2.83 - .Ll.26 12.83. ; j . . .
0 . .'736 '2 ;
.88 ,3 :86
,2 4 ^4
'90 7 190 ; !
*(F/A) and airflow calculated from exhaust composition.
**By subtraction.
P
i
CP
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 35
Engine type JT8D-9
7/22/71 Location TWA Overhaul Facilit Test Cell 5
Engine serial No.P665165B (TWA 39051 Engine total time, hours 8082
Time (hours) since:
Hot section overhaul 3142 Low-speed compressor overhaul 8082
High-speed compressor overhaul 8082 Combustor can replacement 3142
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul 8082
JP-4 Test Fuel
3140
Low-speed turbine overhaul 8082
Additive and concentration N. A.
Inlet air humidity, Ibm HJO/lbm dry air 0. 0164
Relative humidity 79%
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start Finish
77 77
28. 84 28. 84
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, ° F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO^ (wet), ppm**
NOX (wet), ppm
Cruise :METO JTakeoffj
0:00 4:35 | 7:50 j
9,540 11,3401 13,5801
Idle (Reverse '
11:10 j 17:40 ;
840 12,970 !
; [ . T ~ r " ~T r
7210 : 7600 j 8160 j
2960 1 8020 i
10,950 11,200, 11,570- 6,840 : 11,460 ] ,
5220 1.6230..! 77.6(0. 1 840 j 7340 _ .j
118.5 < 131. 5 ! 144.0 ! 27. 1* j 143. 5 !
0.0122 0.0132; 0.01 50*
1.64 1.81 i.2_..02.__,
885 "947" i 1032"
9.1 11.4 14.3
19. .14 11 ..
2._46 .2.65 2.93
1 0 0
58 73 102
554
63 78 106
O.pO&fi 0.0142
1
698 1005 j
0.4 ] 13.5 "
282 i 11 |
_L11 J 2.84.. i
96 '2 . I
2 :.9.3 :
8 14
10 ! 97 ;
i
i
.._. ..
i
!
__
1
_.
.. - i ., . . ..,. r-_
1
*(F/A) and airflow calculated from exhaust composition.
**By subtraction.
P
i
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 36
Date 7/22/71 Location TWA Overhaul Facility. Test Cell 5
Engine type JT8D-9_
Engine serial No.P665165B (TWA 3905) Engine total time, hours 8082
Time (hours) since:
Hot section overhaul 3142 Low-speed compressor overhaul 8082
High-speed compressor overhaul 8082 Combustor can replacement 3142
First stage nozzle guide vane overhaul 3142
High-speed turbine overhaul 8082
Fuel JP-4 Test Fuel Additive and concentration
Low-speed turbine overhaul 8082
N. A.
Inlet air humidity, Ibm H-O/lbm dry air 0. 0174
Relative humidity 79%
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start, Finish
77 76
28. 78 28. 78
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm **
NOX (wet), ppm
Cruise MET O! Take of! Idle
0 : 00 . 4 :40_ _ ] 1 0:15 j 1 4 : 2 5
9,480 li,900i 13,680 i860
^ ' !
7220 i7750 8220 12630
10, 800. 11,270(1 1,600 6,860
5200 6620 i?9lb J840
111. 7 128.2 ,141.0 J28.4*
0~; 0 1 29 0 .0 1 43^6. 01 56 , 0.0082*
1.65 1.86 i 2. 04 |
" i
891 968 '1040 [673
9.1 12.1 14.6 Tb'. 5
24 17 14 |274
2.56 2.81 ;3.07 !l.64
0 0 16 " ~ " '98 "
56 76 :101 "3
5 '6 rs"" ;s
61 82 106 11
Reverse '
18:20 ;
12,560 [
7870 ! 1
11,210 J
7100 ;
133.0 !
070148 i
._-( _i
. .. .
990 ~|
12.9 j '
16 1 1
2.92 I !
0 : ,
82 !
i6 ' 1"
88 !
I
1
:
i
~:~ :. :Ez
~" '
T - -
*(F/A) and airflow calculated from exhaust composition.
**By subtraction.
n
i
N>
O
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 37
Date 7/22/71 Location TWA Overhaul Facility. Test Cell 5
Engine serial No. P665489B (TWA 3981) Engine total time, hours 4413
Time (hours) since:
Hot section overhaul 1027 Low-speed compressor overhaul
Engine type JT8D-9
4413
High-speed compressor overhaul 4413
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul 4413
JP-4 Test Fuel
1027
.Combustor can replacement 1027
Low-speed turbine overhaul 4413
Additive and concentration
N. A.
Inlet air humidity, Ibm H,O/lbm dry air
Relative humidity 78%
0.0141
Start
Inlet air temperature, ° F 71
Atmospheric pressure, in Hg 28. 82
Finish
71
28. 83
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N,
Engine speed, ^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas_pressure, j>sia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm**
NOX (wet), ppm
Cruise METO Takeoff
0;00 13:55 . 28:40
9,500 1^900! 13J>60
i
7170 i 7700 I 8150
10,840; 11,260| 11,570
5180 ! 6570 ! 7810
112.8 128.0 ; 142.3
6 .612 8' 0.01 42 0 . 6T52
869 947 : 974"
9.2 12. 1 14.5
28 16 ! 12
2.61 2.87 |3.07..._..
0 0 ! 0
48 68 ! 88
5 4 ; 5
53 72 ; 93
Idle |
33:40
1,180
3100
7,530
1050
31.7*
0.6092*
673
0.9
417
1 . 83
144
3
8
11
Reverse
39:40
12,660
7870
11,370
7100 ;
i~35. 1
6.0146.
-. ;
j
976
13.1 ,
.16 H
2.97..
0 !
7.5
4
79
..
_
!
i - -
.
I .... ,,
'
...... ^ _ - .
.: 1
._ ! _;
]
r>
i
*(F/A) and airflow calculated from exhaust composition.
**By subtraction.
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 38
Date 7/23/71 Location TWA Overhaul Facility, Test Cell 5
Engine serial No. P665170B (TWA 3907) Engine total time, hours 8088
Time (hours) since:
Hot section overhaul _0 Low-speed compressor overhaul 8088
High-speed compressor overhaul 8088 Combustor can replacement
First stage nozzle guide vane overhaul
High-speed turbine overhaul 8088
Fuel JP-4 Test Fuel
Engine type JT8D-9
0
Low-speed turbine overhaul8088
Additive and concentration N. A.
Inlet air humidity, Ibm H-O/lbm dry air 0.0161
Relative humidity 57%
Start
Inlet air temperature, °F 82
Atmospheric pressure, in Hg 28. 81
Finish
82
28.81
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm ##
NOX (wet), ppm
Cruise METO 'Take of:
0:00 . 11:4 .0_j 1 6i2_5.
9_,540 : 11, 740 [ 13,760,
j
7230 | 7720 8230
1 0,97011 ", 380 ! i 1 7760
5490 ; 6820 ! 8300
111. 1 126. 1 ! 140.4
6 . 01 370.0 1 50 !" 0 . 6 164
1.65 1. 84 ~ 1 2.03
864. . .943 ._' 1019_ .
9.1 11.8 :14.5
16 14 . [10
2.76 3.02 i3..21_.
1 0 Q
62 80 111
3 5 ^5
65 85 116
Idle 'Reverse '
22:50
670
2440_
6490
910
29. 7*
6.0085s!
705
fo.4
1324... .
U.6.9 _
.144
; 9
12
27:00 j
i
i
j
!
8-220 j 1 ]
11,710 T i !
8250 i " " !"
138.9
'6T6l'65i
i
i
i
1005 !
14.4 1
9 !
3.25... i [-:__:
0 ! . 1
. 108 i
i
i
1
i
*(F/A) and airflow calculated from exhaust composition.
**By subtraction.
P
t
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 39
Engine type.
Date 7/26/71 Location TWA Overhaul Facility. Test Cell 5
Engine serial No. GE-l6l-156(TWA 2708)Encine total time, hours 19. 584
Time (hours) since:
Hot section overhaul 1092 Low-speed compressor overhaul
High-speed compressor overhaul 1092 Combustor can replacement
CJ-805
1092
1092
1092
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul 1092
JP-4 Test Fuel Additive and concentration
Low-speed turbine overhaul 1092
N. A.
Inlet air humidity, Ibm H,O/lbm dry air
Relative humidity 73%
0.0099
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start Finish
64 65
29.01 29.01
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO£ (wet), ppm **
NOV (wet), ppm
Cruise !METO
0:00 9:00 ,
8,360 ! 9^100
1
7090 ! 7180
6790 17480
153.6 j!56.8
0.0123:0.0132
2.20 2.28
i
968 '1031
17.0 18.7
60 51
2.58 '2.63
0 |0
51 55
2 2
53 57
Take of i
J&SO
10. 120
7370 j
8620
163.0
0. 0147
2.47
1130
21.0
,48__.._.
2.90
0
Sir
,3
1
$4
Idle
20iOO
400
4530
1060
*32. 4
*0.009
716 ^
0.5
573
1.77
325
3
8
11
_* - _ i
, , , -
1
,
___
-j
- - -i
^ -^
i
~
.._.
.
O
l
*(F/A) and airflow calculated from exhaust composition
**By subtraction
-------
Date 7/26/71 Location
Engine serial No. 630895
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 4Q
Engine type JT3C-6
TWA Overhaul Facility. Test Cell 5
Engine total time, hours 22, 290
Time (hours) since:
Hot section overhaul
5672
5672
High-speed compressor overhaul
Low-speed compressor overhaul
5672 Combust or can replacement 5672
First stage nozzle guide vane overhaul
High-speed turbine overhaul 5672
Fuel JP-4 Test Fuel
5672
Low-speed turbine overhaul 5672
Additive and concentration N. A.
Inlet air humidity, Ibm H _O/lbm dry air
Relative humidity 42%
0.0093
Start
let air temperature, ° F 75
tmospheric pressure, in Hg 29. 01
Finish
82
29.01
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, No
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, ° F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO;> (wet), ppm**
NOX (wet), ppm
CruiseiMETO
0:00 ^2:00 i
6800 1 7920
5730 5920
9120 19270
5730 :6400
144.0 '152. 1
0.0111 0.0117
1.96 2.11
869 925
13.4 " 15.6
38 .28
2.23 2.34
0 0
46 55
6 3
52 58
Takeoff1 Idle !
16:50 119:00
9740 ~]460
h ! -H
6330 J2320
9520 '6220
8120 illlO
167.0 135.0*
0.0137 !0.0088>?
,2.40 t1.10
[1081 f54i
;20.0 {0.7
ill |714
;.2. 76. 1. 53
0 !2160
:13_. i2...
0 ',6
J73 8
t
|
1
1 »
I
:
h - ! J
i - <
1
, ! ...
... ;
i
- - -
1
I
t"
\ i
i
1
|
1
, j
!
1
i
... . ._... .. ,
*(F/A)and airflow calculated from exhaust composition.
**By subtraction.
P
i
N>
-f
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 41
Engine type JT3D-3B
Date "7/27/71 Location TWA Overhaul Facility, Test Cell 5
Engine serial No.P643849B (TWA 2419) Engine total time, hours 11,564
Time (hours) since:
Hot section overhaul 1564 Low-speed compressor overhaul
5936
High-speed compressor overhaul 5936
.Combustor can replacement _5JL3JL
5936
Fuel
First stage nozzle guide vane overhaul.
High-speed turbine overhaul 5936
JP-4 Test Fuel Additive and concentration
Low-speed turbine overhaul 5936
N. A.
Inlet air humidity, Ibm H 2O/lbm dry air 0.0094
Relative humidity
Start
75
Finish
75
Inlet air temperature, °F
Atmospheric pressure, in Hg 28.98 28.98
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, No
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm**
NOV (wet), ppm
137 EFR! Cruise
0:00 14:30
9,100 !11,200
!
5440 !5860
, .... j
9, 160 !9,460
5110 16320
126.0 (142. 3
METO
13:00
13,200
6280
Take of i
28:00
15,420
6680
9,730 10,080
7650 J9400
157.6 173.9
Idle Reverse
34:00
1,100
2160
36:30..
14,900
1
6560
6,150 9,890
1000 ;8940
34.7*
170. 0
0.0113 10.0123 jO. 0135,0.0150 JO. 0080*0. 0146 j
1.37 | i
!
739 797
862
196T
4.8 ,6.5 ^8.5 J10.9
43 20 19
2. 09 2. 27
2,49 _
8 ... .
^J>. 77
1 !12 [3 0
36 47 J74 191
!
i
554 '941
0.3
|649-
1.44
10.25__
2
221 0 j7
38 '49 J75 !91 (9
10.2
12
k, 63
20 (min)
80
1
81
_.._
| t
_j
1
__
I
i
|
i
I
*(F/A) and airflow calculated from exhaust composition.
**By subtraction.
P
l
K>
Vl
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 4Z
Date 7/27/71 Location TWA Overhaul Facility. Test Cell 5
Engine serial No. P648915B (TWA 3031) Engine total time, hours 15.252
Time (hours) since:
Hot section overhaul 0 Low-speed compressor overhaul 15, 252
High-speed compressor overhaul 15,252 Combustor can replacement
Engine type .TT8D-9
0
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul *5, 252
JP-4 Test Fuel
Low-speed turbine overhaul 15, 252
Additive and concentration TM A
Inlet air humidity, Ibm H-O/lbm dry air 0. 0107
Relative humidity 62%
Inlet air temperature, ° F
Atmospheric pressure, in Hg
Start Finish
74 72
28.83 28. 83
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
C02 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
N©2 (wet), ppm *
NOV (wet), ppm
Cruise'METO
0:00 '7:20
9.680 | 11. 370'
j
7280 j 7690
Takeoff) Idl<=>
-Ui3D-
12.850
8050
14i3J3_ 1
1.040
2930
10,960i 11,270 11,510:7150
5600 i6630
7630 .
1010 1
117.5 j 129.3 140.7 34.2
0.013210.0142
1.65 11.79
iJLP_15JL
1.92
^0082
1
887 ;937 986
9.2 11.2 [13.0
15 '11
2.59 J2. 78
1 10
63 ^85
2 2
65 " 87
10
2.93
678
0.7
211
J^65
^fi-\Tf*f Sf* j
2_1:&0. ,
12.770 :
.. ,_n
i
8020 |
11,420 !
7600
140.2
0.0151
!
984
12.9
10
2.95 '
0 42 0
101
12 99
i2 3
103 ; 1 5
3
102
*By subtraction.
i !
:
t
1 ,
t
I
i _ _, .
i
i i
i
j
I
i i
T.7.ZU_ :
! ' ! " "
p
I
-------
AIRCRAFT EMISSIONS BASELINE DATA -TEST No. 43
7/28/71 Location TWA Overhaul Facility, Test Cell 5 _ Engine type
JT8D-9
Engine serial No. P674250B (TWA 5421) Engine total time, hours 3673
Time (hours) since:
Hot section overhaul 0 Low-speed compressor overhaul
High-speed compressor overhaul 3673 Combustor can replacement
3673
First stage nozzle guide vane overhaul
High-speed turbine overhaul 3673
Fuel JP-4 Test Fuel
0
Low-speed turbine overhaul 3673
Additive and concentration N. A.
Inlet air humidity, Ibm H-O/lbm c
Relative humidity 84%
Mode <
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, ° F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm*
NOV (wet), ppm
Irv air 0.0130
rruise >METO
0:0.0 ISrQQ |
9.520 11.020
Pake off
33-00
13.700
; I
7120 .7520
10,890 ;11,150
5270 16150
117.0 J128.0
0.012510.0133
1.65 1.79
J3150
ill,580
Inlet air temperature, °F
Atmospheric pressure, in H
Idle JRe verse 1
40:0.0
860
2600
6,840
18040 |s 50
148.0
0.0151
2.03
31.2
0.0076 '
i
833 !880 970
9.1 10.9 !l4.4
13. .11
8
2. 48. :.2. 67- [2.._92....._
0 ... [0_ _..._fl..._
58 80
5 6
63 86
J120
!l26
662
0.6
45:00.
12.740
"
7870 i
11,400
7320
141.0
0.0144 ,
945
13.0
3.3-1-.. -J-0-. ...
1 . 57 !?. 83
J40_
.3
101 _
i7 ^
!lO il05
Start Finish
66 67
l 28.90 28.91
i
! !
I
t
....
! !
. ^ . ___|
| i
i
i
- . _. i. ... !
i ! " "T
i j
"~ "
i
*By subtraction.
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 44
Date 7/28/71 Location TWA Overhaul Facility. Test Cell 5
Engine type .TTKD-T
Engine serial No.P654074B fTWA 3341) Engine total time, hours 8438
Time (hours) since:
Hot section overhaul 0 Low-speed compressor overhaul 8438
High-speed compressor overhaul 8438 Combustor can replacement
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul 8438
JP-4 Test Fuel
0
Low-speed turbine overhaul 8438
Additive and concentration N. A.
Inlet air humidity, Ibm H-O/lbm dry air
Relative humidity 42%
0.0090
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start
76
Finish
76
28.95 28.95
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N2
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas_pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm*
NOv (wet), ppm
Cruise iMETO
0:00 16:00
9,560 ill, 460
;
7210 J7630
10,980 ;11,280
5620 16750
114.3 128.5
0.0137 0.0146
1.65 1.80
919 979
9.1 H.4
17 11
2.72 2.95
5 1
57 75
3 4
60 79
Takeoff
12:00
12,880
7960
11,580
769_0_
138.5
0.0154
1.94
1033
13.1
!8
,3. 05
'0
95
5
!100
Idle
1.6:00
880
2670
6,910 i
£80 . J
0.0075
702
, .
0.5
231
1.54
97
5
6
11
|
! ' ......
'
i ,
1
1 1
i i
i .. !
i i
I
j 1
! 1
; J
!
1
! i
| ;
1 ; '
1
:
- . - j - .
*By subtrattion.
r>
i
N5
CO
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 45
Date 7/28/71 Location TWA Overhaul Facility, Test Cell 5
Engine serial No. P674250B (TWA 5421)Engine total time, hours 3673
Time (hours) since:
Hot section overhaul 0 . Low-speed compressor overhaul
Engine type JT8D-9
3673
High-speed compressor overhaul 3
Combustor can replacement _ °_
0
First stage nozzle guide vane overhaul _
High-speed turbine overhaul 3673
Fuel JP-4 Test Fnp-1 Additive and concentration
Inlet air humidity, Ibm H 2O/lbm dry air 0.0076
Relative humidity 54%
Low-speed turbine overhaul 3673
N.A.
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start
67
28.98
Finish
68
28.98
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO^ (wet), ppm*
NOV (wet), ppm
Cruise JMETO
0:00 5:00
10,820 111, 990
j_
7360 |7620
11,080 ;l 1,280
6010 16736
126. 3 '135. 0
6~.6T32"6.6l3ir
1.76 1.87
883 918
10.7 12.3
12 ID
2.69 .2.83
1 1
74 93
5 5
79 98
Takeoff
10:00
13,850
8100
11,600
8050
L6T6T50
J2,0.4_ .
£81
14.7
9
3...07..
0
;i35
6
1141
Idle
15:00
870
2650 "^
6800
870
32.2
6.6075"
653
0.6
22Z
[1.56
138
5
6
'11
1
- .. ....
|
i
1
i
.
...
.. . . \
. - .
1
;
!
!
4
" " ~ ^
i
i
" " " ""
, i
P
#By subtraction.
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 46
Date 7/29/71 Location TWA Overhaul Facility. Test
4226
Engine serial No.P654589B (TWA 3705) Engine total time, hours
Time (hours) since:
Hot section overhaul 242 Low-speed compressor overhaul
High-speed compressor overhaul 4226 Combustor can replacement
Engine type JT8D-9
4226
242
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul 4226
JP-4 Test Fuel
242
Low-speed turbine overhaul 4226
Additive and concentration N. A.
Inlet air humidity, Ibm H 2
Q
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 47
Date 7/29/71 Location TWA Overhaul Facility, Test Cell 5 Engine type JT8D-9
Engine serial No. P674266B (TWA 5402) Engine total time, hours _4078
Time (hours) since:
Hot section overhaul 2945 . Low-speed compressor overhaul 4078
High-speed compressor overhaul 4078 Combustor can replacement 2945
First stage nozzle guide vane overhaul 2945
High-speed turbine overhaul 4078
FuelJP-4 Test Fuel
Low-speed turbine overhaul 4078
Additive and concentration
N.A.
Inlet air humidity, Ibm H2O/lbm dry air 0.0107
Relative humidity 86%
Inlet air
temperature,
OF
Start
63
Finish
63
Atmospheric pressure, in Hg 29. 02 29. 02
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/ A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm*
NOV (wet), ppm
bruise 'METO '
0:00 !10:00
9,700 >12,000
1
7130 |7640 .
10,710 ;11,100
5470 J6840
119.0 ] 135. "8
67oi28T67o"l40"
1.65 l".~86~
838 898
9.2 12.0
12.... ;9- -
2.5S 12.81 .
o -io
65 90
3 4
68 94
lake off
20:00 '
13,840
8090
11,420
Idle
25:00
880
2520 '
6,950
8130 |910
149. 3 J32. 4
67o il5 1/0. 007 8
2.02
__
961
14.5
|6
[2..9JL _
io
J117
:5
!122
Reverse !
31:00
13,360 ,
- t -"
7960 ! [
"11,260 '
7770 !
f46.~5
67bT47 r
'
682
0.6
285. ...
120
941
13.7
6 1
2.. 94_
.0 ' _
6 107
7 ;7
.... ...
j.
,
I
1"
i
' "'
1 '
i
|
.. . i
..__.)_ i
j ; ' '
! ' '.
!
P
i
*By subtraction.
-------
Date 7/3Q/71
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 4«
Engine type .TT3D-3B
Location TWA Overhaul Facility. Test Cell 5
Engine serial No. TWA No. 3130
Time (hours) since:
Hot section overhaul 3939
Engine total time, hours 10. 673
High-speed compressor overhaul
Low-speed compressor overhaul
3939 Combustor can replacement
3939
3939
3939
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul 3939
JP-4 Test Fuel Additive and concentration
Low-speed turbine overhaul 3939
N. A.
Inlet air humidity, Ibm H2O/lbm dry air 0.0074
Relative humidity 65%
Inlet air temperature, ° F
Atmospheric pressure, in Hg
Start Finish
_61 60
29. 09 29.10
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, ° F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NC"2 (wet)» PPm **
NOX (wet), ppm
. 37 EHt Cruise
0:00 j.5;Q_Q_._.
8..960 j 10,860.,
,
I
5330 15800
9000 9270
4980 16070
127.4 J143.0
0.0109 iO.0118
1. 37
705 752
4.8 6.5
43- IS
2, 16... ^2.34.
4 . . '0 .
30 43
8 6
38 49
MET OlTakeod Idle Reverse
,L5_iQ(L.
13.060
6110
9540
-32J.O.O.,
1 5^3 20
6580
35:30
1. 040
2050
98~60 f5950
^7390 J9180 ]960
158. 5
0.0130
813
8.4
1-9
2, 58.
io
;61
4
165
175.0 J30.6*
0.0146 0.0087*
L . 1
fll.l
Is
*-
189
541
0.4
1, 80
91Q
|4 _ ;7
40:00 .
14,440 _
6430
9650
8670
169.2
0.0142
864
10. 1
6
2. .80 _
0
76
5
n
.
i
1 .
_ _
i
i
j
- - - j - -
i
i
i i
*(F/A) and airflow calculated from exhaust composition.
#*By subtraction.
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 49
Date 7/30/71 Location TWA Overhaul Facility, Test Cell 5
Engine serial No. P610670B (TWA 2201)Engine total time, hours 26.595
Time (hours) since:
Hot section overhaul 0 Low-speed compressor overhaul
High-speed compressor overhaul 7494 Combustor can replacement
Engine type JT4A-11
7494
7494
Fuel
First stage nozzle guide vane overhaul 3033
High-speed turbine overhaul 7494
J.P-4 Test Fuel Additive and concentration
Low-speed turbine overhaul 7494
N.A.,
Inlet air humidity, Ibm H2O/lbm dry air 0.0080
Relative humidity 50%
Inlet air temperature, ° F
Atmospheric pressure, in Hg
Start
66
Finish
67
29.09 29.09
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, Nj
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
C02 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO£ (wet), ppm*
NOV (wet), ppm
Cruise !MFTO
0:00 !12:30
9,720 111,500
!
5580 i5840
8170 8400
8,050 19^530
205.7 1218.8
0.0109 10.0121
2.01 2.22
880 977
13,6 16.4
32 29
2.22 2.46
0 0
51 64
4 4
55 68
Ta k<* nff
21:10
14,620
6450
8830
12,920
240.5
0.0149
2.61
1184
21.2
26_.
3.00
o. .
103
i3
;106
Idle
24:00
620
2240
5210
1,300 .
61.3
0.0059
543
0.6
1412
ri.22
r850
:3
6
9
Reverse
31:50
14,000
6280
8690
^200
236. 7
0.0143
1137
20. 3
25.
2.88
0
90
4
194
.
11
I
1
i
!
-i
t
!
f
/
t
! !
~"~ " i
*By subtraction.
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 50
Date 8/2/71 Location TWA Overhaul Facility, Test Cell 5
Engine serial No. P649125B (TWA 2860)Engine totai time, hours 14,289
Time (hours) since:
Hot section overhaul 3433 Low-speed compressor overhaul
Engine type JT8D-1
8843
High-speed compressor overhaul 8843
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul 8843
JP-4 Test Fuel
8843
.Combustor can replacement S843
Low-speed turbine overhaul 8843
Additive and concentration N. A.
Inlet air humidity, Ibm H,O/lbm dry air 0. 0127
Relative humidity 49%
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start Finiah
83 83
28.96 28.96
Cruise ME TO JTake of f ildle [Reverse
f\ _ f\ /\ ' 1 *~i _ f\ f\ o A~" /\~/\ I i r* . /\ /\' -4 *^ . s\ s\
Mode
.
Time, min
Thrust, Ibf (observed) _______________
Shaft horsepower (observed) _
Engine speed, N
Engine speed,
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/ A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia _
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
(wet), ppm *
0:00
9,660
11 ' °_P I IM 0_j~35:00
" lT,48otl 2,520 j 800
;47:00
112,420
7310 "
11,080
564^0
U4.6_
P.0137
1.65
7720
T17400
6"780~
7990 | 25_80_ I 79_50_
rr;5iots;T7o"~! 117490
.j.
7590 880
7590
127. ILL 133^ 132.2
O.P.147 ^10,0158 10.0074
1.79 1.90" |
919_
9Tl
986 i!026 i741
11.2 '12.6 0.5
NOX (wet), ppm
16 U3 |12_.
2.80 42,96... .j.3,.07_
1 so |p_
6lI__"3iZ^jJ052
5 . "..'Is ~ |5 1
66 89 illO
J
J202
74 ~
134.4
0.0157
1038
j.
12.5
*By subtraction.
3M JL3__ .
3,. 12
j.
1.04
5
109
j 104 [___
~i
o
UJ
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 51
Date 8/2/71 LocationTWA Overhaul Facility. Test Cell 5
Engine serial No.643558 (TWA 2367) Engine total time, hours 4158
Time (hours) since:
Hot section overhaul 4158 Low-speed compressor overhaul
High-speed compressor overhaul 4158 Combustor can replacement
Engine type JT3D-3B
4158
4158
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul 4158
JP-4 Test Fuel
4158
Low-speed turbine overhaul 4158
Additive and concentration
N. A.
Inlet air humidity, Ibm H-O/lbm dry air
Relative humidity 68%
0.0120
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start Finish
72 72
28.94 28.94
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratlb (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas j>ressure^psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm**
NOX (wet), ppm
1.37 EH*! Cruise
0:00 !4:15
9,040 111, 180
i
5420 J5840
9130 19420
5030 (6290
METO
Takeoffl Idle Reverse
9:30 |14:45
13,300
6220
9680
r7630
15,440
22:00
26:00 i
960 jl5,000~|
"
6670 |2030
9980 r
9360 1
r5870
1020" "'
6550 I
1
j
\
i 1
9900 ! i !
8950 j
126.0J.142.3 j.158. 5 [173.9 [32.0* ;171.0 !
0.0111 iO.0123 j.0.0134 io.0149
1.37 il.50 .1.66
730 790
856
4.8 6.5 8.6
52 26 i 15
2. 21 2.44 ;2. 65
12 2 ! 0
34 45 '" : 62
3 5 3
37 - : 50 1 65
i
1.84
_ ..
959
11.0
25
^.89
i
i
3.0089*10.0145 i 1
1 . L !
536
0. 3
645
1.80
0 710
85 4
2
87
4
8
) i
930
10.3
20
2.81 ,
0 I
i
!
' ' !
76 X 1
79 "' " ' ' ! I "-
*(F/A) and airflow calculated from exhaust composition.
**By subtraction.
P
i
OJ
(ft
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 52
Date 8/3/71 Location TWA Overhaul Facility, Test Cell 5
Engine serial No.P674379B (TWA 5420) Engine total time, hours 3686
Time (hours) since:
Hot section overhaul 4°^ Low-speed compressor overhaul
Engine type JT8D-9
3686
3686
High-speed compressor overhaul
First stage nozzle guide vane overhaul
High-speed turbine overhaul
3686
,Combustor can replacement
3686
Low-speed turbine overhaul 3686
Fuel JP~4 Test Fuel
Additive and concentration N. A.
Inlet air humidity, Ibm H-O/lbm dry air
Relative humidity 60%
0.0129
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start
78
28.97 28. 97
Finish
78
Mode
Time, min
Thrust, Ibf (observed)
Shaftwiiorsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm*
NOX (wet), ppm
*By subtraction.
Cruise; METO |Takeof£
0:00...:5.:QO._il_0:_Op. .
9,640 : 11.820J 13,780
i
7250 17730 8260
1 0,8 8 0 ' 1 1 , 2 1 dl 1 1 ,~57 0
5540 6840 1 8220
116.5 132.2 j 147.4
0.0132" 0.01 44" 0.0155
880 '945 "Tib'iar"
9.0 11.9 ;14.5
11 12 ill
2.69 2.93 .3.14
0 0 0
62 86 119
5 4 .6
67 90 125
Idle
J 5:0.0
900
' 1 " ' "' ' 1 ' " " "~ " ""
] '
2710 |
6,960 ' ~
880
32-3 i ,
0.0076
1
1
I- -- --! i
680 , ;
0.6
318 1
i,6o ; _._,.
167 (max) !
5
7
12
-. _ . ...»,«. .
t ^_
;
- - j --
)
! , . -
i ""i -
f t -
! i
!'~" "
1
1 ,
i :
i
p
IP
6?
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 53
Date 8/3/71 Location TWA Overhaul Facility. Test Cell 5
Engine serial No.P674379B (TWA 5420) Engine total time, hours 3686
Time (hours) since:
Hot section overhaul 460 Low-speed compressor overhaul 3686
High-speed compressor overhaul 3686 Combustor can replacement
First stage nozzle guide vane overhaul
High-speed turbine overhaul 3686
Fuel JP-4 Test Fuel
Engine type JT8D-9
460
Low-speed turbine overhaul 3686
Additive and concentration 0.1% by volume CI-2
Inlet air humidity, Ibm H2O/lbm dry air 0.01Z9
Relative humidity 54%
Start
Inlet air temperature, °F 80
Atmospheric pressure, in Hg 28.97
Finish
80
28.97
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas jpressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm*
NOV (wet), ppm
*By subtraction.
Cruise !METO
0:00 :3:30
i,700 i 11^5.00
7250 7790
10,890 11,260
5480 :6910
116.7 132.9
0.0130 0.0144
878 !950
9.0 11.9
26 _ 19 -
2.66 :2. 98
0 0
61 89
5 2
66 91
Takeoff!
8:00
43^7401
1
.....
8260
11,590
8 3 00
146.6
0.0157
il031
!14.3
'15.
J3..2Q. _
;o
:A!9_.
4
123
Idle
13;00
J9_00
2720 __J
6950
890
t32. 3
0.0076
i_ . _. _
£85__
0.6
345...
1...59
r194(ma
.5..
7
12
?cj
__.-_ J
_ ...
i
1
*
j
i
. .... ...;
. ,i
! 1
.. j 1 .
i
1
i
!
p
t
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 54
Location TWA Overhaul Facility. Test Cell 5
Date 8/3/71
Engine serial No. TWA No. 2220
Time (hours) since:
Hot section overhaul 329
Engine type JT4A-11
Engine total time, hours 27, 324
Low-speed compressor overhaul
7619
Fuel
High-speed compressor overhaul 7619 Combuator can replacement 329 (222-0533, -0534, -0535)
First stage nozzle guide vane overhaul 329 Low-speed turbine overhaul 7619
High-speed turbine overhaul 7619
JP-4 Test Fuel Additive and concentration N. A.
Inlet air humidity, Ibm H2O/lbm dry air 0.0116
Relative humidity 61%
Inlet air temperature, ° F
Atmospheric pressure, in Hg
Start
75
28.95
Finish
75
28.95
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N,
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure^jpsia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm*
NOV (wet), ppm
*By subtraction.
C"rni
23:30
600
2090
5250
1,360
56.7
0.0067
^574
0.1
464
1,35
870
3
6
9
R pV£* 7* fi«3
29:00
13t760
"6250
8900
12,300
231. 5
0.0148
. _.
1157
120.4
'22
2.97. .
2
93
2
'95
t
-
. ..- ...
.
-
..... i
..
" '
.
"" " ""
I
UJ
GO
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 55
Date 8/3/71
Location TWA Overhaul Facility, Test Cell 5
Engine serial No. TWA No. 2220
Time (hours) since:
Hot section overhaul 329
Engine type JT4A-11
Engine total time, hours 27, 324
Fuel
High-speed compressor overhaul
First stage nozzle guide vane overhaul
High-speed turbine overhaul 7619
JP-4 Test Fuel
Low-speed compressor overhaul 7619
7619 .Combustor can replacement 329 (222-0533. -0534,
-0535)
329
Low-speed turbine overhaul 7619
Additive and concentration Q. 1% b
ri-2
Inlet air humidity, Ibm H2O/lbm dry air 0.0ll7
Relative humidity 63%
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start,
74
2ft Q<5
Finish
73
2R 05
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, ° F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NOg (wet), ppm*
NOX (wet), ppm
*By subtraction.
Cruise METO Takeoff 1 Idle
0:00 4:35 !10:15 15:00
9,480 "ill, 020 14~460 600
_._. T j..__
5550 |5790 i6410 jilOO
8290 :8520 ~%990 5220 n
8,000 :9,330 112,950 1,380
199. 3 212.4 j236. 2 57. 2
0.0112 0.0122 0.0152 0.0067
889 977 11193 1556
13.1 15.9 21. 4 JO. 7
39 33 i23 ,48.3.
2.25 :2.41 J2. 9.9. . |l...35
1 0 !q. ;929
46 58 :97 3
2 4 3 6
48 62 !100 9
Reverse | !
24:00 I
14,060 : "
l ' 4
^340" ': '] T
8850 I
12,640 ' "I ' 1 ! - '
234.2 j "j __^
0.0150 ; ' '
i '
1179 [
21.0 | :
28 ' \
\ - ~ ! -
2. 96_._ i I - - ] 4
I 1 ' 1 ~ "1
94 ~ ; "1 i " "
96 : ~ ' !
r>
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 56
Date 8/3/71 Location TWA Overhaul Facility. Test Cell 5
Engine serial No. TWA No. 2220
Time (hours) since:
Hot section overhaul 329
Engine type JT4A-11
Engine total time, hours 27. 324
7619
Low-speed compressor overhaul _
7619 Combustor can replacement 329 (222-0533. -0534, -0535)
First stage nozzle guide vane overhaul 329 Low-speed turbine overhaul 7619 ;_
High-speed compressor overhaul
High-speed turbine overhaul 7619
Fuel JP-4 Test Fuel Additive and concentration
0. 0125% bv volume C1.7.
Inlet air humidity, Ibm H2O/lbm dry air 0.0116
Relative humidity 63%
Inlet air temperature, ° F
Atmospheric pressure, in Hg
Start Finish
74 72
28.95 28. Q5
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
COz (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
N©2 (wet), ppm*
NOV (wet), ppm
Cruise iMETO takeoff Idle j
0:00 :4:00 19:30 14:30
9,500 10,960j 14,440 i600
_ : _ _;i i~_~
5550 '5770 J6400 J2100
8350 .8.520 .j 8970 ;5230.
8,000 9,310 112^820 ' 1,360
200.3 211.9 ] 236. 0 J57. 2
0.0111 '0.0122 "1676 1 52 10.0066
; 1
894 *973 !lT88"~ \55S"~~
13.4 15.8 21.3 JO. 7
30 26 :25 463
2.30 2.53 j3. 05 11.45
1 :0 ;0 ...... 774
46 57 ;95. ;3
4 5 3 i6
50 62 98 9
Reverse
18:30 j
14,340
cjzir."r'Yc.zi-
6J7_0 ' T
8.950 . ! ,|...
12,86.0 : 1.
235,2 ,
0.0152 i !
|
1182 '': 1
21.3
27
3.05
1 .. ..
94.. .; .._ s.._ _....
3 . i
97
i
i
,
- j- -
"" "\
I
.. .... ..,
1
i
i
*By subtraction.
O
o
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 57
Date 8/4/71
Location TWA Overhaul Facility, Test Cell 5
Engine type _ CJ-805
Engine serial No. GE-161-108 (TWA2695fengine total time, hours 22,738
Time (hours) since:
Hot section overhaul 0 . Low-speed compressor overhaul 0
High-speed compressor overhaul N. A. Combustor can replacement 0 (323-041 (L -0411, -0412)
First stage nozzle guide vane overhaul 0 Low-speed turbine overhaul 0
Fuel
High-speed turbine overhaul N. A.
JP-4 Test Fuel Additive and concentration
N. A.
Inlet air humidity, Ibm HJO/lbm dry air
Relative humidity 72%
0.0153
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start Finish
75 J75
29.06 29.06
Mode
Time, min
Thrust, ibf (observed)
Shaft horsepower (observed)
Engine speed, N,
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, ° F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm*
NOX (wet), ppm
*By subtraction.
Cruise iMETO
0:00 ; 4:00
8,080 8,820
7120 17180
1
6670 17300"'
148.2 ;152.3
0.0125 0.0133
968 1022
16.5 17.9
52 48
2.55 2.70
0 0
53 61
7 5
60 ' 66
Takeoff! Idle ! i
10|00 j 15:00 ; . j ... ' . I
10, 000 |400 I 1 1
1 " r * ' ; " " r " "
7380 J4510 ;
8590 J1090 '! "" " : "j |'~ "
162.5 J43.9* j i i .
0.bl47~tb.0069* : i
i i "" ' ! 1 "" "" ~
I ! : *~ '
1128 J716 " " "T" ~J ~ "
20.8 io.5 1 1
46 i472
[2.96 11-31 1 _
0 1340 ! i
75 "":3 ----.- ..- i -. - _.
;81 ,7 ' "1" ' i """ "
p
I
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 58
Date 8/4/71 Location TWA Overhaul Facility. Test Cell 5
Engine serial No.GE-161 108 (TWA26Q5) Engine total time, hour a ??s 738
Time (hours) since:
Hot section overhaul 0 Low-speed compressor overhaul
High-speed compressor overhaul N. A. Combustor can replacement 0 (323-0410. -0411, -0412)
Engine type r.T-ftQS
0
0
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul N. A.
JP-4 Test Fuel Additive and concentration
Low-speed turbine overhaul.
0 1% bv volume fT-2
Inlet air humidity, Ibm H ,0/lbm c
Relative humidity 68%
Mode (
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N?
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm**
NOX (wet), ppm
Irv air 0. 0150
ruise IMETO
0:00 3:00
8,160 8,820
7130 7180
6680 '7290
147.5 ;151.8
0.0128 ; 6. 01 33"
Take of fj
Inlet air temperature, °F
Atmospheric pressure, in H
Idle 1
6:00 !10:00
10,020
400
7380 |4520
8620 [1090
162. 1 144. 5*
"670 1 48 jO "."006 8*
; j
982 1029
16.7 17.9
68 67
2.61 .2.71
0 0
55 61
3 2
58 63
'.1137
20.9
60
J2.91. _
o
;75
5 ""'
';80
736 i
0.5
454 ... ....
1.3.0.
337
3
5
8
Start Finish
77 77
g 29.05 29.05
i !
*
.
-
" 1 '
- - --
1
j_
...
_.
. _
>
_.. .. 1
[
I
1
! "~" " "*"" "
I
i - i - ; - -
P
t
*(F/A) and air rate calculated from exhaust composition.
**By subtraction.
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 59
Date 8/4/71
Location TWA Overhaul
Tost r>11
Engine type CJ-805
Engine serial No.GE 161 1Q8 (TWA 2695)Engine total time, hours 22,738
Time (hours) since:
Hot section overhaul 0 Low-speed compressor overhaul 0
High-speed compressor overhaul NTA. Combustor can replacement 0 (323-Q410.r -0411, -0412)
Low-speed turbine overhaul J_
Fuel
First stage nozzle guide vane overhaul 0
High-speed turbine overhaul N. A.
JP-4 Test Fuel Additive and concentration 0. 0125% by volume CI-2
Inlet air humidity, Ibm H JO/lbm dry air
Relative humidity 66%
0.0154
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start
77
Finish
78
29.04 29.04
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gasj>ressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO£ (wet), ppm**
NOX (wet), ppm
Cruise METO JTakeoff
0:00 3:00 ]6iOO
8,260 8,800 ! 10,000
i !
7150 i7200 17410
" "T" '
6780 T7390 '8620
149.2 J152. 8 J162.6
0.0126 0.0134 0.0147
999 '1040 i ri4F~~
16.9 18.0 120.9
56 54 i 53
2.56 2.75 13.00
0 0 !0
56 61 i75
5 5 :6
61 66 :81
Idle
1Q;00
i
1
4510 | i
1 - i
1080 ' !
43.4*
1 6. 0669*
725-' ' ;
r0.5~ '4 ~
!471
1.43
;345 ' |
.4 , s
7 - |
1
' - . . .j
: i
i
i -
:
i
r
"""'" 1
t
j
j
i
j
_ _j
. - +..- ""^
i
1
*(F/A) and airflow calculated from exhaust composition.
** By subtraction.
O
!
-^
IP
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 60
Date 8/4/71 Location TWA Overhaul Facility. Test Cell 5
Engine type CJ-805
Engine serial No.GE 161 108 (TWA 2695)Engine total time, hours 22,738
Time (hours) since:
Hot section overhaul _0 ^ Low-speed compressor overhaul
High-speed compressor overhaul N. A. Combustor can replacement 0 (323-0410, -0411,
First stage nozzle guide vane overhaul ° Low-speed turbine overhaul 2
0
-0412)
High-speed turbine overhaul N. A.
Fuel JP-4 Test Fuel Additive and concentration
Inlet air humidity, Ibm H2O/lbm dry air 0.0154
Relative humidity 66%
0. 1% by volume CI-2
Start
Inlet air temperature, °F 78
Atmospheric pressure, in He 29.04
Finish
78
29.04
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, No
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
COZ (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO£ (wet), ppm ##
NOX (wet), ppm
Cruise METO
0:00 3:00
8,080 8,820 "
7140 7210
6650 T7320
147.8 152.5
0~. 01 25, 0.0 133
981 1042
16.4 18.0
65 64
2._53 .,2.70
0 0
50 57
4 4
54 61
Takeoff! Idle ' i
5jOO J9:00 ( : . i
"lo7bo6_J4b6" j ; :
| I ! !
7400 j 4510 | i ! ;
1 ' ~ 1 ' ;' '
8590 ;1090 ! I " ~ ; "~
162.0 ;44. 5* i ' ,
0.0147 io.00684 : ; " -t -..-.
i i
i ' * ^ ^
1134 :728 i | i
20. 8 iO.5 i i i
165 J4.92 _ .]._.. . !.._... !
12.98 !l.'38 i ! i
!6 '372' ; I " "
7i " ,2 " 1 ; " " j
4 ,6 .
|75 :8 I i '|
*(F/A) and airflow calculated from exhaust composition.
##By subtraction.
P
i
.U
-------
AIRCRAFT EMISSIONS BASELINE DATA -TEST No.
Date 8/4/71 Location TWA Overhaul Facility. Test Cell 5
Engine type
Engine serial No.P643558B (TWA 2367) Engine total time, houra _i!5_8
Time (hours) since:
Hot section overhaul 4158 Low-speed compressor overhaul 4158
High-speed compressor overhaul 4158 Combustor can replacement 415JL
Fuel
First stage nozzle guide vane overhaul __4158
High-speed turbine overhaul 4158
JP-4 Test Fuel
Low-speed turbine overhaul 4158
Additive and concentration N. A.
Inlet air humidity, Ibm H2<0/lbm dry air 0.0116
Relative humidity
Inlet air temperature,
Atmospheric pressure
°F
, inHg
Start
68
Finish
67
29.05 29.05
Mode_
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, Nj
Engine speed, No
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm*
NOV (wet), ppm
*By subtraction.
.37 EF^Cruise
0:00 5;00
9,000 ill, 180
j_
5380 J5830
9160 [9370
5010 ;6310
126.2 143.6
0.0110 10.0122
1.37
716 777
4.6 6.5
47 25
2.24 -2.48
26... 26
33 43
2 3
35 46
METO
.Tiflft
13,300
6200
9630
(7610
160.0
0.0132
844
8.5
,12
2.69L
2.6
;57
4
61
Take of i
11:00..
15,420
6550
9930
9330
174.4
0.0148
*939
10.9
11. _
3..0J ..
!l6...
j8_3
2
i85
Idle
15:00
960
2020
£890 ;
1000
30.8
0.0090
536
0.3
627. . ^
1.68...
1240..
is
|5
8
_ _
.
"
1
j
!
... - 4
. ,
S- .
'*""*""
p
I
^
(A
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 62
Date 8/4/71
Location TWA Overhaul Facility. Test Cell 5
Engine type .TT3D-3R
Engine serial No.P643558B (TWA 23671 Engine total time, hour a 4158
Time (hours) since:
Hot section overhaul 4158 Low-speed compressor overhaul 4158
High-speed compressor overhaul 4158 Combustor can replacement,
4158
Low-speed turbine overhaul 41.58_
Fuel
First stage nozzle guide vane overhaul 4158
High-speed turbine overhaul 4158
JP-4 Test Fuel Additive and concentration 0. 1% bv volume CI-2
Inlet air humidity, Ibm H JO/lbm dry air 0.0124
Relative humidity 81%
Inlet air temperature, ° F
Atmospheric pressure, in Hg
Start
66
29.04
Finish
66
29.04
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC*
NO (wet), ppm
NO2 (wet), ppm**
NOX (wet), ppm
*Hydrocarbon data masked by oil
^*By subtraction.
l_17 FPp.j Cruise
0:O.Q. J6:0fl
9.080 ill. 200
1
5390 45830
9020 19370
5100 16300
127.3 |143.7
0.0111 0.0122
1.37
;
725 1775
4.8 6.5
66 34
2. 22 ;2. 48
31 42
2 2
33 44
Leak.
METO
IIWUL-
13.420
6210
9630
17660
161.0
0.0132
844
18.5
;16_ ..
1..68 . .
J55
3
58
Takeoff
11:0.0...
15.500
6660
9930
9340
^l 75. 4
p. 0148
r
937
110v9
11
E.9i
!
77
3
80
Idle
16:00
980
2020
5880
r!030
31.8
0.0090
J540
X 3
>74__
1,66
(*
4
8
H
.. .
j ..
~
-
i
j
, I
"
.
I
1
. - '
..., .
p
I
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 63
Date 8/4/71 Location TWA Overhaul Facility, Test Cell 5
Engine serial No.P643558B (TWA 2367) Engine total time, hours 4158
Time (hours) since:
Hot section overhaul 4158 Low-speed compressor overhaul
Engine type JT3D-3B
4158
High-speed compressor overhaul 4158
4158
.Combustor can replacement 4158
First stage nozzle guide vane overhaul
High-speed turbine overhaul 4158
Fuel JP-4 Test Fuel Additive and concentration
Low-speed turbine overhaul 4158
0. 0125% bv volume CI-2
Inlet air humidity, Ibm H-O/lbm <
Relative humidity 81%
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, Ng
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC *
NO (wet), ppm
NO£ (wet), ppm #*
NOV (wet), ppm
iryair 0.0124
U7EFR1 Cruise
METO
Start Finish
Inlet air temperature, °F
Atmospheric pressure, in H
Takeoff Idle
0:00 5:00 J9:00 11:30
9,000 111,250
5350 15830
9020 19480
5120 J6320
126.3 1143.7
13,250
-
6200
9630
7610
160.0
0.0113 0.0122 .0.0132
1.37
7~14 "" T777
844
4. 8 6. 5 8. 5
72.. :53 .. 126.
2r 26 12,47
[ j
29 45. .. _59_._
i ;2
30 47
J3 .
i62
15,460
!6660 j
9950
9360
'175. 4
0.0148
13:00 , . j
980
i
2015
5910 i
1000 '
31.8 j
0.0087 i
_._ i __i ___!__._
i
939 550"
JJ.O
22-
^ n?.
0.3
[675- -
r
1. 62
*.. w~~
A
3 5
86 b
.
.
I
66 66
ff 29. 04 29.
04
i
i
I
i
i
r
,
u
i
f
P
i
*Hydrocarbon data obscured by oil leak.
**By subtractioii.
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 64
Date 8/5/71 Location TWA Overhaul Facility, Test Cell 5
Engine type JT3D-3B
16.564
Engine serial NoJ3643434B (TWA 23321 Engine total time, hours 16,564
Time (hours) since:
Hot section overhaul 16, 564 _ Low-speed compressor overhaul _____
High-speed compressor overhaul 16,564 Corobustor can replacement
First stage nozzle guide vane overhaul 16, 564 Low-speed turbine overhaul 16, 564
High-speed turbine overhaul 16. 564 _
Fuel JP-4 Test Fuel _ Additive and concentration
7694
N.
Inlet air humidity, Ibm H JO/lbm dry air 0. 0139
Relative humidity 63%
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start Finish
77 17
29. 14 29. 12
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, ° F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm #
NOX (wet), ppm
137 EFRJ Cruise
0:0.0 |4U)Q..__
8,820 1L.040
5460 i5840
9170 19410
5120 '6320
124.4 :141.7
0.0114 :0.0124
1 . 38 1 . 50
747 806
5.0 6.5
43... :26 _
2.34 ,2.52
50. 38
35 48 _.. _
4 2
39 50
MET 0 -take off
.6.10.0... .
.13,310
6250
9680
10; 00
15^10
6660
9970 j
7800 J9490
158.9 173.2 j
0.6"! 33 |b.0i52
1.66 1.84
!
874
8.6
,19-
957
10.9
34.
,
26 ....... 24..
i64_ J8.8_. ._
2 13
!66 91
Idle Jteversrt Tntfti- 1
13:00
950
16:00 ..
2050 J6640
5870 ;9910
980 !9540 ""
30.6
173.2
0.0080 ;0.0153
...
552
0.3
625- _
1,57
1060
ry
7
9
964
11.0
zs
3. 04 .
27
81....
2
83
19:00
5000
8900
4050
110.0
0.0102 H
687
3.5
65
2. 10
5.0 _
3-° -
I
TntAi- 7
22:OD
5f QQX)
4380 ,
8480
2980
IB9.0
Tntpr ^
24:00
2,950
349X>
7820
^990
b3. 2
0.0093 10.0087
-
639
2.2
594 ""
1.1
92 M?
^ ]
22 .
1
23
U.7.9 ._
10.4 ....
14_ _
.,.
*By subtraction.
CD
-------
Date 8/5/71
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 65
Engine type JT8D-1
Location TWA Overhaul Facility. Test Cell 5
Q45
Engine serial No. P649185B (TWA 3078) Engine total time, hours 15.745
Time (hours) since:
Hot section overhaul 2685 Low-speed compressor overhaul 11
High-speed compressor overhaul 11. 945 Combustor can replacement
First stage nozzle guide vane overhaul 11,945 Low-speed turbine overhaul 11, 945
High-speed turbine overhaul 11, 945
Fuel JP-4 Test Fuel Additive and concentration N. A.
2685
Inlet air humidity, Ibm H2O/lbm dry air 0.0127
Relative humidity 72%
Start
71
Finish
70
Inlet air temperature, °F
Atmospheric pressure, in Hg 29,10 29.11
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, ° F
Exhaust gas pressure, j>sia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO£ (wet), ppm *
NOX (wet), ppm
Cruise
0:00
9,560
METO
7:OCL_
11,500
7300 1 7750
11,000
115.6
0.0135
1.65
11,34(T
6810
L130.0
Takeod Idle
isTidb
8140
J8:JP.
1,050
2970
11,630 7,350
7940
141. 1
0.0145 0.0156
1.80 1.95
; '
865
9.4
29
2.75
0
53
5"
58
925
11.5
20
2.95
;o
988
13.5
16
3. 16
0
1060
37. 1
0.0079J
649
0.7
388
1.64
^84
87 7
Inter. 1 Inter. 2 Inter. 2
.24:45. 27:45 .29:40., .
1,520 ,2,500 '5.020
3540
4390
8^,030 18,970
1400 i2010 j
42.4
0.0092
684
1.1
300
1.89
52 ~
Tz '"
54.9
0.01 02
732 '
1.9 .
162
2.09
22
14
5 T6 8 |7 18
74 |93 15 J19 22
5840
9,990
3020
80.4
0.0104
694
4.3.
56
2. 13
6
27
Inte r-T-4
32:3jQ
7.120
6600
1JL530
4090
97,8
0.0114
768
6.2
39
L2. 33
1
34 ""
1 14
28 ~"|38~'~"
_ .-..- .
.
.
.
.
; .. ... .
*By subtraction.
NO
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 66
Location TWA Overhaul Facility. Test Cell 5
Engine type JT8D-1
Date 8/5/71
Engine serial No.P649185B (TWA 3078) Engine total time,hourslj
Time (hours) since:
Hot section overhaul 268 5 Low-speed compressor overhaul 11, 945
High-speed compressor overhaul H» 945 Combustor can replacement 2685
First stage nozzle guide vane overhaul H>945 Low-speed turbine overhaul 11,945
Fuel
High-speed turbine overhaul 11, 945*
JP-4 Test Fuel Additive and concentration
0. 1% bv volume CI-2
Inlet air humidity, Ibm H,O/lbm dry air
Relative humidity 69%
0.0121
Start
69
Finish
69
Inlet air temperature, ° F
Atmospheric pressure, in Hg 29. 11 29.11
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, ^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm*
NOX (wet), ppm
Cruise METO ^akeoff
0:00 '6:30 19:15
9,540 11,460
7250 "~|7 740
10,940 ill, 320
5590 IS 780
0.0135~!0,0145.
I
13,060
£110
Idle
12:00
1,080
3020
11,580 7350
7840
140.2
1070
36.6
JCL0J155. 10.Q0.8J
862 ;919 977
9.3 11.5 13.4
43 37
2.71 2.91 "
0 0
50 67
3 3
53 70
23
3. 10
0 "
J83
"5" ' "
88
\
\ -
i
i
' "" " '
j !
649
0.7
397 i
1.68
110
9
5"
14
I
...
;
i
i
!
1
i
-
-- "
1 ' ""
1
_
^By subtraction.
0
I
in
o
-------
AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 67
Date ft/5/71
Location TWA
Test Cell 5
Engine type .TT8D-1
Engine serial No. P649185B (TWA 3078)Engine total time, hours 15. 745
Time (hours) since:
Hot section overhaul 2685 Low-speed compressor overhaul
High-speed compressor overhaul 11.945 ^Combustor can replacement
11.945
2685
First stage nozzle guide vane overhaul
High-speed turbine overhaul H> 945
Fuel JP-4
11,945
Low-speed turbine overhaul 1.1, 945
Additive and concentration 0. 0125% by volume CI-2
Inlet air humidity, Ibm H -O/lbm dry air
Relative humidity 66%
0.0119
Start
Inlet air temperature, ° F 69
Atmospheric pressure, in Hg 29. 11
Finish
69
29.11
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N?
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gasjpressure, psia
CO (wet), ppm
COz (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NOg (wet), ppm*
NOX (wet), ppm
*By subtraction.
Cruise 'METO
0:00 ^3:35
9,680 J 11,480
|
7300 [7730
11,010 li,30CP
5660 6790
116. 7 . 129. 7
Oioi35~ 0.0145"
858 919
9.8 11.5
42 35
2.76 .2.96
0 .0
54 69
3 5
57 74
Takeoff! Idle
..6iQCL iSjQO
12.980 1 1,040
_ _j_ - ...
8090 12990
11,570'7300
7870 J1060
140.4 |35. 7
'o7oT56 [6.0082
"975 j~658'~
13.4 TO. 7
,31 1 3.88...
a.jti...U.m ..
o :so
86 17
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AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 68
6025
Engine type JT8D-Q
Date 8/6/71 Location TWA Overhaul Facility. Test Cell 5
Engine serial No.P665408B (TWA 3959) Engine total time, hours
Time (hours) since:
Hot section overhaul 2937 Low-speed compressor overhaul 6025
High-speed compressor overhaul 6025 Combustor can replacement 2937
2937
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul 6025
JP-4 Test Fiigl Additive and concentration
Low-speed turbine overhaul 6025
N A
Inlet air humidity, Ibm H~O/lbm dry air
Relative humidity 83%
0.0113
Start
Finish
65
Inlet air temperature, °F 65
Atmospheric pressure, in Hg 29. 12 29.12
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO^ (wet), ppm*
NOX (wet), ppm
Idle Inter 1
0:00 6:00
880 :i,85'6"1
2730 | 3800
6, 840 '8, 230 ~
930 1570
32.9 |47.5~~
0.0079 6.0692
666 698
0.6 1.3
362 169
1.65 1.91
140 22
11 17
2 5
13 22
Inter 2 Inter 3 ilnter 4
f?:.OQ
'2,960
4660
8,920
1840
59. 6 "
"o._qo8_6~
12:00
4,090
5310
9,450 {
2420
71.7
6V0094
I
,610 648
2.3
,88
1.80
'13
3.3
55
1 , 94
4
18 22
'3" 7 "
:21 29
14:30
5,180
5780
9,780
2950
M-II
0.0100
685
4.3
29
!"
29
6
35
Cruise METO
16:00 .19:30
9,640 jll,380
7580
10,680
5540
118.2
0.0130
.. ..
85 1_
9.4
18....
2.65
0
62
5
67
7710
10,740
6.5 IJL _
131.2
0.0138
1
1 - n
r
900
ril.3
11
2.80.._
o._ ..
76
5
81
Takeoff
22:00 1
13^10
8190 j
11,400 |
8370__ j .
150.2
0.0155
|
993 ;
14, 7 j .
6
3.1.4 _. __. t
0 !
Ill
-.
119 '
*By subtraction.
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AIRCRAFT EMISSIONS BASELINE DATA-TEST No.69
Date 8/9/71
Location TWA Overhaul Facility. Test <""<»11 5
Engine type JT8D-9
0
Engine serial No. P665704B (TWA 4033) Engine total time, hours
Time (hours) since:
Hot section overhaul 0 . Low-speed compressor overhaul 0
High-speed compressor overhaul Q Combustor can replacement
0
Fuel
First stage nozzle guide vane overhaul
High-speed turbine overhaul 0
.TP-4 Tpgt TTW1
Low-speed turbine overhaul 0
Additive and concentration N. A.
Inlet air humidity, Ibm H 2O/lbm dry air 0. 0121
Relative humidity 41%
Inlet air temperature, °F
Start
87
Finish
87
Atmospheric pressure, in Hg 29. 05 29. 05
Mode
Iruise ;METQlTakp.off! Idle friter 1
2
Tn^t- 4
»v Tntfiy A
.
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N
Engine speed,
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, ° F
Exhaust gas temperature, °F
Exhaust gas pressure, psia _
0:0.0 ;6;QO I
12:00 |17:00 ;23:00
88Q jl,2j6.
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AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 70
Location TWA Overhaul Farility, Tpaf-
Date 8/11/71
Engine serial No. (TWA 2260)
Time (hours) since:
Hot section overhaul 3145
Engine total time, hours Rr 055
Engine type JT4A-11
Fuel
8055
Low-speed compressor overhaul
High-speed compressor overhaul 8055 Combustor can replacement 3145
First stage nozzle guide vane overhaul 8055
High-speed turbine overhaul 8055
JP-4 Test Fuel
Low-speed turbine overhaul 8055
Additive and concentration
N A
Inlet air humidity, Ibm H-O/lbm dry air
Relative humidity 56%
0.0130
Inlet air temperature, °F
Atmospheric pressure, in Hg
Start, Finish
76 81
28.98 28.98
Mode
Cruisd METO' Takeoftf Idle ilnter. 1 Inter. Zfrnter. 3,Tntftr. 4JTntpr 5!Tntg»T-
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N,
Engine speed, N£
Fuel flow, Ibm/hr
Gas generator air flow, Ibm/sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, ° F
Exhaust gas temperature, °F
^Exhaust gas pressure, psia
CO (wet), ppm
CO2 (wet),
0.00, :14:00 J28_:00 !35:00 43:00 47:00 52:30
9, 360 _lQt 84Q..J14t.22.g-k2Q L.5 OP -
5,660 i5, 890
8, 280 :8, 520
6J.500...!2JL.L.5JP_
8t.97_Q ;5, 240
7,850 9, 110^ Jl2j5lO.il, 300
204.0 215.0 1237.0 ^8.0
o. 0107 o. 0118"67qi47" ;6.0062
1.97 2.14 J2.58 i
57:00 59:00 |b5-:0a__
.l,.7JjQ_.12,_QOO
13, 3.10....
?a-5_QP
2,0.00
35.1
0.0065
6x.2SfiL 7a_QP. J7,.430_ [7t 73Q
!2, 170 .2,..3^
92.7 98.9 J11U8 1.34.0 jl 57.0
|0.0065 J0.006_6 Q. 0074)0._0070]0..0078
._- j.._. __ _ t
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm *
NOX (wet), ppm
* By Subtraction
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AIRCRAFT EMISSIONS BASELINE DATA-TEST No.
Date 8/11/71 Location TWA Overall Facility. Test Cell 5
Engine type JT3D-3B
Engine serial No. (TWA No. 2537) Engine total time, hours 17,359
Time (hours) since:
Hot section overhaul 0
Fuel
High-speed compressor overhaul
First stage nozzle guide vane overhaul 17. 359
High-speed turbine overhaul 17, 359*
JP-4 Test Fuel Additive and concentration
Low-speed compressor overhaul 17, 359 _
17.359 Combustor can replacement J17.359
Low-speed turbine overhaul 17, 359
N.A.
Inlet air humidity, Ibm HjO/lbm dry air
Relative humidity 49%
0.0137
Start
J3
Finish
83
Inlet air temperature, °F
Atmospheric pressure, in Hg 28. 96 28. 96
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, °F
Exhaust gas pressure, psia
CO (wet), ppm
COZ (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm *
NOX (wet), ppm
L37E PRtrui s e
i.OQ.._.-J7:.Qfl
,930 ilO, 860
470 J5850 _j
?270 ;9480
3100 16310
24.0 1139.2
3.0114 ;0.0126
.37 1.50
METO
ikon .
13,000
6230
9770
7590
154.4
0. 0137
1.65
765 835 J8~83
,.8 6.4 J8.4
10 28 ._ 120 ..... ...
J.3JL 12,54 J2..7J5...
?0 !54 . Il6
12 52 J66
.Takeof;
47:00.
15+2&Q
6670
10, ..Q40,
9440 ""
171.3
6.0153
1 . 84
f Idle
52:OJQ
880
.
_,
L240
579Q .._.
900
29.4
6. 0085"
1 . . .
f?97 672
10.9
las.
l._.0_7
14
91
0.3
743
1,73 ...
992
3
L 1336
43 53 '69 94 \)
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#By Subtraction
NOTE: THIS IS THE FIRST OF TWO PAGES DESCRIBING TEST NO. 71
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AIRCRAFT EMISSIONS BASELINE DATA-TEST No. 71 (Cont'd)
Date 8/11/71 Location TWA Overall Facility. Test Cell 5 Engine type JT3D-3B
Engine serial No. (TWA No. 2537) Engine total time, hours 17.359
Time (hours) since:
Hot section overhaul 0 Low-speed compressor overhaul 17. 359
High-speed compressor overhaul 17.359 Combustor can replacement 17.359
Fuel
First stage nozzle guide vane overhaul 17.359
High-speed turbine overhaul 17, 359
JP-4 Test Fuel Additive and concentration
Low-speed turbine overhaul 17.359
N. A
Inlet air humidity, Ibm H JO/lbm dry air
Relative humidity 49%
0.0137
Inlet air temperature, ° F
Atmospheric pressure, in Hg
Start. Finish
83 83
28.96 28.96
Mode
Time, min
Thrust, Ibf (observed)
Shaft horsepower (observed)
Engine speed, N.
Engine speed, N^
Fuel flow, Ibm/hr
Gas generator air flow, Ibm /sec
Calculated (F/A)
Engine pressure ratio (EPR)
Turbine inlet temperature, °F
Exhaust gas temperature, ° F
Exhaust gas pressure, psia
CO (wet), ppm
C02 (wet), %
Hydrocarbons (wet), ppmC
NO (wet), ppm
NO2 (wet), ppm *
NOX (wet), ppm
Inter. 1 'Inter. 2
57:00 59:30 4.
Inter. 3
62:00
1,240 1,500 11,750
'
2330 12550
6420 i6770
1200 1340
36.0 140.7
0.0093 '0.0091
5..71. __5_a3.
0.4 0.5
642_ .566 -
1 . 88 ,1 . 85
688 562
6- ;7 . _
4 3.
10 10
2750
7070
L470
Inter. 4i Inter. 5 Inter. 6 Inter . 7
£4:00
2,000
2920
7300
15.90 _
44.5 J48.3
6.009210.0091
590
0.6
67:00 69:30
2^00 4, 000
i
3220 3980
7680 J8210
L84Q_._ 12470..
55.9 72.0 1
0..0091 D. 0095
:
'
5.9.SL
0.6
,527. £52
l..&7___JUa2. -
<496 36 Q.
!_. £___
i. L
11 12
1617 £22 1
0.9 |l .ft
QhO. k62... J
1.. 83.._[.9.4
.256. 9.2 ._
10 |4
i_ 5
14 19
74: O.Q
7^000
5_0_2_Q
S22ft__
4090
I P8. .9..
0. 0104
700
b.s , ,
'>(,
2. 11.
5.6
50
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*By Subtraction
NOTE: THIS IS THE SECOND OF TWO PAGES DESCRIBING TEST NO. 71
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APPENDIX D
Fuel Specifications
-------
TABLE D-l. SPECIFICATIONS OF FUELS USED DURING AIRCRAFT
TURBINE EMISSIONS MEASUREMENT PROGRAM
Data Item Kelly AFB JP-4 TWA Mobil Jet A
Numerical hydrogen/carbon ratio 1.995 1.968
API gravity, ° at 60° F ( ASTM D-287) 49.5 44.1
Sulfur, % (ASTM D-l29) 0.00 0.05
F.I.A. (ASTM D-1319)
% Aroma tics 16. 7 12. 7
% Olefins 0.8 1.9
% Saturates 82.5 85.4
Distillation (ASTM D-86)
Initial Boiling Point, °F 140 340
10% 196 370
20% 212 382
30% 224 394
40% 244 406
50% 260 418
60% 280 428
70% 295 440
80% 339 460
90% 385 480
95% 417 495
End Point, °F 442 520
Recovery, % 99-0
Residue, % 1.0
Note: In an independent evaluation supplied to SwRI by TWA officials, the
results were almost identical to the SwRI test.
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