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.
                                   11

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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.
                                 111

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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,
                                     8

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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
                                10

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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.







                                   11

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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
                                   12

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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
                                   13

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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
                                14

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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
                                 15

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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.








                                   16

-------
    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




                                   17

-------
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
                                 18

-------
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
"Tn r+- Kl.. V, (1,1- ! 4 "
jt^oA^-
.75%
IOQ'4
.FUak* Tow*A Xd V*
U. GJvou.w.4 141*
tA.4t "
loovl
u^ic;rnV^ -
28"
Zfc

.J10
287
;:S::
i 2:Q
i 127
iX7 1


2.57
i.Ofc
3.29
l,5(b
1.40
|2.t 2>
2. '3 7
3.06
3.2 6
l.fcS
1.32
2. 07

1 1 S
V24
52
Zfo
Z&
. <°5-
2>2
Z 4"1
25


r • '•
5EOUS EM1S
1 • ji ! i [
' > |TT ; }
; i ' i i ! _L
..'. .lOj
; in
._i_i2i.
iiZJQj-
• \ :O:
i O!
, i !0i
. _.L o.
Tsk'si"
; I '
. i i i i ; !
, ' !
;4-6
33
39
;4-S
4-5
289
1 ;32. i
i !2'8!
• ' iS
i !2>:Z'
i 34
['366' T


2._4. 2
3.07
3.2S
l.fc 1
1.30
2.05

sia'y"
A! 3.3"
2.08 !
i
73.
\ O3
\A\ 	
33
24
Zfc
feCo'l
.90,
A 0 1 1
22
SIGNS FR01
i ! 1
WDR.<
1 ' >
' 4-'^£.!
4-iQ,
44


5CARB<

; O
0
! iO'
.i...;._Q,_.
"Isi6;t
! ' ; : i i
cLo 0*)e.T) i

31
it,
2-31
27;
:27i
3 2" 3
L 4-'O; !
i2;C>; ^
' 2J 1 i !
:Z4
21 1 '
21 7

Q.OZ (_U)ET ),
2.54 j
3,1 7 .
3.42
1.6.8
1,33
2. 32
NO*
95
I OS
3 1
ZZ

L 2^52
:3. 1 0
3,34
lilO,
1.9 4
CWET) ,
.7.2 .
1 O4 :
29

2

4-3 0
4_\ :
14- \
4-2
4-5
2 SO;
.0
i 0 :
; o
6

3^m
;
27

24-
2.9
32
i9 9
; ...i:*;.
r v 3

r 2m 	 : 	
fc7
32.
2S
25
^oet),^-
fi>3
97
24 i
foO
83
"
r._._.^....i.7.!F .._
r 7 9
-79 I
1 » B !
. 34
zs
28

71
1 °\ 1 1'
2 7 j
BOPROP M
9 id

.: .....j. ...4

4
3
--i 	 --
q j
""•'"o
	 .O I


4-2
. 4-4 :
'ZS\> 2;9;|

_.__^
31
2 :
1.7 2 ,
1,43 ..
2.V 9
!
! ..§
o
4
4
isz


4-9
38
_32
55
279


2,53
3.1 1
3.3 1
».47
1.34-
2.04-
j
	 i
i
fc & :
97
9 9 i
""34 !
29 '
za
•llii
Z8
2 9 i

\ 1 8
1 2(o
3 1
Zl
~3O
	 - - |

-------
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
\c.Sv f\l\j %vi c < V
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	 1 8 1 ZO 2.1

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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.i—in—I.	—	-^•••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 — 	 	
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f
i
i
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. .. .. i !
i !
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: 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
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j
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j
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— |
1
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- - 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
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. _ 	


i • . |.. . . .
i j
j !
i
- .. i
;
1


i 	 -
i
i l
t 1
1 ~| "
_ ., f

._. . 1
1

i
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- • ( ' " •
	 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



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-j

- - -i


	
^ -^

i



— ~ —
	
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.





	


                                                                                                      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
:

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- - -









1



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t"


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i



1
|
1


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!
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




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| 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




|




	



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'

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1
1 1
• i i
i .. !
i i
I
j 1
! 1
; J
!

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: — 	
- — . - j -• • . • 	
*By subtrattion.
                                                                                                 r>
                                                                                                  i
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-------
                       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

	


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i 	
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1







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!
!
— 	 	 	 — 4 	
" " ~ 	 ^
•
i
i


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, 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



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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 .
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i






j










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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

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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

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-------
                       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






	



	 	



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-------
                       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











-





	





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                                                                                                       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




_ _

.



























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—













S- .


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                                                                                                        (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 .. 	 	



	
















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.

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-------
                        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
:4 9
90 16


-
	 i
i
I



t.._ .. . i 	
: _ ._
:
"1 ~
.. .. ! ..._.
1 i
< 	 -1- - -
i







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[ ... _
	





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i i
i
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i
i

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* "~ I 	
i
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i
i
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                                                                                                        p
                                                                                                        I
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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.
                                                                                                       p
                                                                                                        I
                                                                                                       tn

-------
                        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.
-------
                        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
                                                                                                            P
                                                                                                             i
                                                                                                            Ul

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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 \)
t
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#By Subtraction
                     NOTE:  THIS IS THE FIRST OF TWO PAGES DESCRIBING TEST NO. 71
                                                                                                        P
                                                                                                         i
                                                                                                        in
                                                                                                        l/i

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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
I i
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f j
j
1 ' f "

j
1 ~" "1
I i
i
f -— •
: i
i
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i I 	 -
L : T "
32 ! 	 : "~
                                                                                                        P
                                                                                                        i
 *By Subtraction
                 NOTE:  THIS IS THE SECOND OF TWO PAGES DESCRIBING TEST NO. 71

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   APPENDIX D




Fuel  Specifications

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   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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