UNCLASSIFIED AD NUMBER LIMITATION CHANGES62. Fuel Pump Start Transient Performance, Firing 06E . ....

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Approved for public release; distribution isunlimited.

Distribution authorized to DoD only;Administrative/Operational Use; DEC 1968. Otherrequests shall be referred to NASA MarshallSpace Flight Center, Huntsville, AL.

AEDC ltr 12 Jul 1974

AEDC-TR-68-238

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FLIGHT SUPPORT TESTING

OF THE J-2 ROCKET ENGINE IN PROPULSION ENGINE TEST CELL (J-4)

(TESTS J4-1901-03 THROUGH J4-1901-06)

%* <<.?

N. R. Vettfe£^;

ARO, Inc. %v

December 1968 ThisdccL;.-^;-):';^"^...

Each trans merit Mi Alabama 35812

LARGE ROCKET FACILITY

ARNOLD ENGINEERING DEVELOPMENT CENTER

AIR FORCE SYSTEMS COMMAND

ARNOLD AIR FORCE STATION, TENNESSEE

PH0F3ETY OF U. S. 113 FCHC3

P<10ÜC3-Sa-C-0001

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/mm When U. S. Government drawings specifications, or other data arc used for any purpose other than a definitely related Government procurement operation, the Government thereby incurs no responsibility nor any obligation whatsoever, and the fact thai the Government may have formulated, furnished, or in any way supplied the said drawings, specifications, or other data, is not to be regarded by implication or otherwise, or in any manner licensing the holder or any other person or corporation, or conveying any rights or permission to manufacture, use, or sell any patented invention that may in any way be related thereto.

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References to named commercial products in this report are not to be considered in any sense as an endorsement of the product by the United States Air Force or the Government.

AEDC-TR-68-238

FLIGHT SUPPORT TESTING

OF THE J-2 ROCKET ENGINE IN

PROPULSION ENGINE TEST CELL (J-4)

(TESTS J4-1901-03 THROUGH J4-1901-06)

N. R. Vetter

ARO, Inc.

This docLinr.eniKacbein s^rcvsd forDirblic^n

■■ - -.' its distribution is unlimited. wF*^

Each trans ment

AEDC-TR-68-238

FOREWORD

The work reported herein was sponsored by the National Aeronautics and Space Administration (NASA), Marshall Space Flight Center (MSFC) (I-E-J), under System 92IE, Project 9194.

The results of the tests presented were obtained by ARO, Inc.-, y

(a subsidiary of Sverdrup & Parcel and Associates, Inc.), contract oper- ator of the Arnold Engineering Development Center (AEDC), Air Force Systems Command (AFSC), Arnold Air Force Station, Tennessee, ;under Contract F40600-69-C-0001. Program direction was provided by. ,.Vt NASA/MSFC; engineering liaison was provided by North American.-Rock- well Corporation, Rocketdyne Division, manufacturer of the J-2 rocket engine, and McDonneli Douglas Corporation, Douglas Aircraft Company, Missile and Space Systems Division, manufacturer of the S-IVB stage. The testing reported herein was conducted between July 23 and August 15, 1968, in Propulsion Engine Test Cell (J-4) of the Large Rocket Facility (LRF) under ARO Project No. KA1901. The manuscript was submitted for publication on September 25, 1968.

Information in this report is embargoed under the Department of State International Traffic in Arms Regulations. This report may be released to foreign governments by departments or agencies of the U. S. Government subject to approval of NASA, Marshall Space Flight Center (I-E-J), or higher authority. Private individuals or firms re- quire a Department of State export license.

This technical report has been reviewed and is approved.

Edgar D. Smith Roy R. Croy, Jr. Major, USAF Colonel, USAF AF Representative, LRF Director of Test Directorate of Test

n

AEDC-TR-68-238

ABSTRACT

■Fourteen firings of the Rocketdyne J-2 rocket engine (S/N J-2036-1) were conducted at pressure altitude conditions during four test periods (J4-1901-03 through J4-1901-06) between July 23 and August 15, 1968, in Test Cell J-4 of the Large Rocket Facility. This testing was in support of the J-2 engine application to the S-II and S-IVB stages of the Saturn V vehicle. The firings were accomplished at pressure altitudes between 78, 000 and 110, 000 ft at engine start. The primary objective of these firings was to evaluate engine start transients under various combinations of starting conditions with start tank energy being the major variable. The total accumulated firing duration for these four test periods was 223. 2 sec.

This documejrf is pubj set to special export controls and each>transmittal to foreign govefwi flents oft .foreign natio Kus may be m\ade onlv^ jfrffh prior appr *Sgl of NAää , Marshal Space FTTght Center (I-E-J), Hunts*

y<nlU, Alabama 35812.

This document lo:bc*sn —proved for jDublic rejeaje

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A'EDC-TR-68-238

CONTENTS

Pag?

ABSTRACT iii NOMENCLATURE ix

I. INTRODUCTION 1 II. APPARATUS 1

III. PROCEDURE 7 IV. RESULTS AND DISCUSSION 8 V. SUMMARY OF RESULTS 17

REFERENCES 17

APPENDIXES

I. ILLUSTRATIONS

Figure

1. Test Cell J-4 Complex 21

2. Test CellJ-4, Artist's Conception 22

3. Engine Details 23

4. S-IVB Battleship Stage/J-2 Engine Schematic 24

5. Engine Schematic 25

6. Engine Start Logic Schematic 26

7. Engine Start and Shutdown Sequence 27

8. Engine Start Conditions for the Pump Inlets, Start Tank, and Helium Tank 29

9. Thermal Conditioning History of Engine Components, Firing 03A 31

10. Engine Transient Operation, Firing 03A 32

11. Fuel Pump Start Transient Performance, Firing 03A . . 36

12. Engine Ambient and Combustion Chamber Pressure, Firing 03A 37

13. Thermal Conditioning History of Engine Components, Firing 03B 38

14. Engine Transient Operation, Firing 03B 39

AEDC-TR-68-238

Figure Page'

15. Fuel Pump Start Transient Performance, Firing 03B . . 43'

.16. Engine Ambient and Combustion Chamber Pressure, Firing 03B 44

17. Thermal Conditioning History of Engine Components, Firing 03C 45

18. Engine Transient Operation, Firing 03C 46

19. Fuel Pump Start Transient Performance, Firing 03C . . 50

20. Engine Ambient and Combustion Chamber Pressure, Firing 03C 51

21. Thermal Conditioning History of Engine Components, Firing 03D 52

22. Engine Transient Operation, Firing 03D 53

23. Fuel Pump Start Transient Performance, Firing 03D . . 55

24. Engine Ambient and Combustion Chamber Pressure, Firing 03D 56




28. Engine Ambient and Combustion Chamber Pressure, Firing 04A ' ; 63

29. Thermal Conditioning History of Engine Components,- Firing 04B 64

30. Engine Transient Operation, Firing 04B 65

31. Fuel Pump Start Transient Performance, Firing 04B . . 69

32. Engine Ambient and Combustion Chamber Pressure, Firing 04B . . . : . 70





VI

AEDO-TR-68-238

Figure Page

37. Thermal Conditioning History of Engine Components, Firing 04D 78



4GL Engine Ambient and Combustion Chamber Pressure, .1.. Firing 04D 82


4-2. Engine Transient Operation, Firing 05A 84

43. Engine Ambient and Combustion Chamber Pressure, : . Firing 05A 86




47. Engine Ambient and Combustion Chamber Pressure,, Firing 06A 93

48. Thermal Conditioning History of Engine Components, Firing 06B 94

> 49. Engine Transient Operation, Firing 06B 95

50. Fuel Pump Start Transient Performance, Firing 06B . . 99"

51. Engine Ambient and Combustion Chamber Pressure, Firing 06B 100





56. Thermal Conditioning History of Engine Components, i Firing 06D 108



Vll

AEDC-TR-68-238

Figure Page

59. Engine Ambient and Combustion Chamber Pressure, Firing 06D 114

60. Thermal Conditioning History of Engine Components, Firing 06E 115

61. Engine Transient Operation, Firing 06E 116

62. Fuel Pump Start Transient Performance, Firing 06E . . 118

63. Engine Ambient and Combustion Chamber Pressure, Firing 06E 119

II. TABLES

I. Major Engine Components 120

II. Summary of Engine Orifices 121

III. Engine Modifications (Between Tests J4-1901-03 and J4-1901-06) 122

IV. Engine Component Replacements (Between Tests J4-1901-03 and J4-1901-06) 122

V. Engine Purge and Component Conditioning Sequence 123

VI. Summary of Test Requirements and Results .... 124

VII. Engine Valve Timings 12T

VIII. Engine Performance Summary 129

III. INSTRUMENTATION 130

IV. METHOD OF CALCULATION (PERFORMANCE .PROGRAM) 143

Vlll

AEDC-TR-68-238

NOMENCLATURE

A Area, in.2

ASI Augmented spark igniter

ES ' Engine start, designated as the time that helium control and ignition phase solenoids are energized

GG Gas generator

MOV Main oxidizer valve

STDV Start tank discharge valve

tg Defined as the time at which the opening signal is applied to the start tank discharge valve solenoid

VSC Vibration safety counts, defined as the time at which engine vibration was in excess of 150 g rms in a 960- to 6000-Hz

, . frequency range

SUBSCRIPTS

f Force

m Mass

t Throat

IX

AEDC.-TR-68-238

SECTION I

INTRODUCTION

Testing of the Rocketdyne J-2 rocket engine using an S-IVB battleship stage has been in progress since July, 1966, at AEDC in support of J-2 engine application on the Saturn IB and Saturn V launch vehicles for the NASA Apollo Program. The 14 firings reported herein were conducted during test periods J4-1901-03 through J4-1901-06 in Propul- sion Engine Test Cell.(J-4) (Figs, i and 2, Appendix I) of the Large Rocket Facility (LRF). These firings were to investigate engine start transients for S-IVB first burn and 80-min orbital restarts and S-1I starts utilizing a 230, 000-lbf-thrust configuration engine. The firings were accomplished at pressure altitudes ranging from 78, 000 to 110, 000 ft (geometric pressure altitude, Z, Ref. 1) at engine start. Engine components were conditioned to temperatures predicted for an S-IVB first burn, 80-min restart, or S-II start. Data collected to ac- complish the test objectives are presented herein. The results of the previous test period are presented in Ref. 2.

SECTIONS APPARATUS

2.1 TEST ARTICLE

The test article was a J-2 rocket engine (Fig. 3) designed and developed by Rocketdyne Division of North American Rockwell Corpora- tion. The engine uses liquid oxygen and liquid hydrogen as propellants and has a thrust rating of 230, 000 lbf at an oxidizer-to-fuel mixture ratio of 5.5. An S-IVB battleship stage was used to supply propellants to the engine. A schematic of the battleship stage is presented in Fig. 4.

Listings of major engine components and engine, orifices for this test period are presented in Tables I and II, respectively (Appendix II), All engine modifications and component replacements performed since the previous test period are presented in Tables III and IV, respectively.

AEDC-TR-68-238

2.1.1 J-2 Rocket Engine

The J-2 rocket engine (Figs. 3 and 5, Ref. 3) features the following major components:

1. Thrust Chamber - The tubular-walled, bell-shaped thrust ' chamber consists of an 18. 6-in. -diam combustion chamber (8. 0 in. long from the injector mounting to the throat inlet) with a characteristic length (L*) of 24. 6 in., a 170. 4-in.2

throat area, and a divergent nozzle with an expansion ratio of 27. 1. Thrust chamber length (from the injector flange to the nozzle exit) is 107 in. Cooling is accomplished by the circula- tion of engine fuel flow downward from the fuel manifold through 180 tubes and then upward through 360 tubes to the injector.

2. Thrust Chamber Injector - The injector is a concentric-orificed (concentric fuel orifices around the oxidizer post orifices), porous-faced injector. Fuel and oxidizer injector orifice areas are 25. 0 and 16. 0 in. , respectively. The porous material, forming the injector face, allows approximately 3. 5 percent of total fuel flow to transpiration cool the face of the injector.

3. Augmented Spark Igniter - The augmented spark igniter unit is mounted on the thrust chamber injector and supplies the initial energy source to ignite propellants in the main combustion chamber. The augmented spark igniter chamber is an integral part of the thrust chamber injector. Fuel and oxidizer are ig- nited in the combustion area by two spark plugs.

4. Fuel Turbopump - The turbopump is composed of a two-stage turbine-stator assembly, an inducer, and a seven-stage axial- flow pump. The pump is self lubricated and nominally produces, at rated conditions, a head rise of 38, 215 ft (1248 psia) of liquid hydrogen at a flow rate of 8585 gpm for a rotor speed of 27, 265 rpm.

5. Oxidizer Turbopump - The turbopump is composed of a two- stage turbine-stator assembly and a single-stage centrifugal pump. The pump is self lubricated and nominally produces, at rated conditions, a head rise of 2170 ft (1107 psia) of liquid oxygen at a flow rate of 2965 gpm for a rotor speed of 8688 rpm.

6. Gas Generator - The gas generator consists of a combustion chamber containing two spark plugs, a pneumatically operated control valve containing oxidizer and fuel poppets, and an injector assembly. The oxidizer and fuel poppets provide a fuel lead to the gas generator combustion chamber. The high energy gases produced by the gas generator are directed to the fuel

AEDC-TR-68-238

turbine and then to the oxidizer turbine (through the turbine crossover duct) before being exhausted into the thrust chamber at an area ratio (A/At) of approximately 11.

7. Propellant Utilization Valve - The motor-driven propellant utilization valve is mounted on the oxidizer turbopump and by- passes liquid oxygen from the discharge to the inlet side of the pump to vary engine mixture ratio.

8. Propellant Bleed Valves - The pneumatically operated fuel and oxidizer bleed valves provide pressure relief for the boiloff of propellants trapped between the battleship stage prevalves and main propellant valves at engine shutdown.

9. Integral Hydrogen Start Tank and Helium Tank - The integral tanks consist of a 7258-in.3 sphere for hydrogen with a 1000-in.3 sphere for helium located within it. Pressurized gaseous hydrogen in the start tank provides the initial energy source for spinning the propellant turbopumps during engine start. The helium tank provides a helium pressure supply to the engine pneumatic control system.

10. Oxidizer Turbine Bypass Valve - The pneumatically actuated oxidizer turbine bypass valve provides control of the fuel

' turbine exhaust gases directed to the oxidizer turbine in order to control the oxidizer-to-fuel turbine spinup relationship. The fuel turbine exhaust gases which bypass the oxidizer turbine are discharged into the thrust chamber.

11. Main Oxidizer Valve - The main oxidizer valve is a pneumatically actuated, two-stage, butterfly-type valve located in the oxidizer high pressure duct between the turbopump and main injector. The first-stage actuator positions the main oxidizer valve at the 14-deg position to obtain initial thrust chamber ignition; the second-stage actuator ramps the main oxidizer valve full open to accelerate the engine to main-stage operation.

12. Main Fuel Valve - The main fuel valve is a pneumatically actuated butterfly-type valve located in the fuel high pressure duct between the turbopump and the fuel manifold.

13. Pneumatic Control Package - The pneumatic control package controls all pneumatically operated engine valves and purges.

14. Electrical Control Assembly - The electrical control assembly provides the electrical logic required for proper sequencing of engine components during operation.

AEDC-TR-68-238

15. Primary and Auxiliary Flight Instrumentation Packages -The instrumentation packages contain sensors required to monitor critical engine parameters. The packages provide environ-' mental control for the sensors.

2.1.2 S-IVB Battleship Stage

The S-IVB battleship stage is approximately 22 ft in diameter and 49 ft long and has a maximum propellant capacity of 46, 000 lb of liquid hydrogen and 199, 000 lb of liquid oxygen. The propellant tanks, fuel above oxidizer, are separated by a common bulkhead. Propellant prevalves, in the low pressure ducts (external to the tanks) interfacing the stage and the engine, retain propellant in the stage until being admitted into the engine to the main propellant valves and serve as emergency engine shutoff valves. Propellant recirculation pumps in both fuel and oxidizer tanks are utilized to circulate propellants through the low pressure ducts and turbopumps before engine start to stabilize hardware temperatures near normal operating levels and to prevent propellant temperature stratification. Vent and relief valve systems are provided for both propellant tanks.

Pressurization of the fuel and oxidizer tanks was accomplished by facility systems using hydrogen and helium, respectively, as the pres- surizing gases. The engine-supplied gaseous hydrogen for fuel tank pressurization during S-IVB and S-II flight was routed to the facility venting system.

2.2 TEST CELL

Test Cell J-4, Fig. 2, is a vertically oriented test unit designed for static testing of liquid-propellant rocket engines and propulsion systems at pressure altitudes of 100, 000 ft. The basic cell construction provides a 1. 5-million-lbf-thrust capacity. The cell consists of four major components (1) test capsule, 48 ft in diameter and 82 ft in height, situated at grade level and containing the test article; (2) spray chamber, 100 ft in diameter and 250 ft in depth, located directly beneath the test capsule to provide exhaust gas cooling and dehumidification; (3) coolant water, steam, nitrogen (gaseous and liquid), hydrogen (gaseous and liquid), and liquid oxygen and gaseous helium storage and delivery systems for operation of the cell and test article; and (4) control building, containing test article controls, test cell controls, and data acquisition equipment. Exhaust machinery is connected with the spray chamber and maintains a minimum test cell pressure before and after the engine firing and exhausts the products of combustion from the

AEDC-TFT-68-238

engine firing. Before a firing, the facility steam ejector, in series with the exhaust machinery, provides a pressure altitude of 100, 000 ft in the test capsule. A detailed description of the test cell is presented in Ref. 4.

The battleship stage and the J-2 engine were oriented vertically downward on the centerline of the diffus er-steam ejector assembly. This assembly consisted of a diffuser duct (20 ft in diameter by 150 ft in length), a centerbody steam ejector within the diffuser duct, a diffuser insert (13. 5 ft in diameter by 30 ft in length) at the inlet to the diffuser duct, and a gaseous nitrogen annular ejector above the diffuser insert. The diffuser insert was provided for dynamic pressure re- covery of the engine exhaust gases and to maintain engine ambient pressure altitude (attained by the steam ejector) during the engine firing. The annular ejector was provided to suppress steam recirculation into the test capsule during steam ejector shutdown. The test cell was also equipped with (1) a gaseous nitrogen purge system for continuously inerting the normal air in-leakage of the cell; (2) a gaseous nitrogen re- press urization system for raising test cell pressure, after engine cutoff, to a level equal to spray chamber pressure and for rapid emergency inerting of the capsule; and (3) a spray chamber liquid nitrogen supply and distribution manifold for initially inerting the spray chamber and exhaust ducting and. for increasing the molecular weight of the hydrogen- rich exhaust products.

An engine component conditioning system was provided for temperature conditioning engine components. The conditioning system utilized a liquid hydrogen-helium heat exchanger to provide cold helium gas for component conditioning. Engine components requiring temperature conditioning were the thrust chamber, crossover duct, start tank discharge valve (test 05 only), and main oxidizer valve second-stage actuator. Helium was routed internally through the crossover duct and tubular-walled thrust chamber and externally over the start tank discharge valve. Main oxidizer valve conditioning was achieved by opening the prevalves and permitting propellants into the engine.

2.3 INSTRUMENTATION

Instrumentation systems were provided to measure engine, stage, and-facility parameters. The engine instrumentation was comprised of (1) flight instrumentation for the measurement of critical engine parameters and (2) facility instrumentation which was provided to verify the flight instrumentation and to measure additional engine parameters. The flight instrumentation was provided and calibrated by the engine manufacturer; facility instrumentation was initially calibrated and periodically

AEDC-TR-68-238

recalibrated at AEDC. Appendix III contains a list of all measured test parameters and the locations of selected sensing points.

Pressure measurements were made using strain-gage and capacitance-type pressure transducers. Temperature measurements were made using resistance temperature transducers and thermocouples. Oxidizer arid fuel turbopump shaft speeds were sensed by magnetic pick- up. Fuel and oxidizer flow rates to the engine were measured by turbine-type flowmeters which are an integral part of the engine. The propellant recirculation flow rates were also monitored with turbine- type flowmeters. Vibrations were measured by accelerometers mounted on the oxidizer injector dome and on the turbopumps. Primary engine and stage valves were instrumented with linear potentiometers and limit switches.

The data acquisition systems were calibrated by (1) precision electrical shunt resistance substitution for the pressure transducers and resistance temperature transducer units; (2) voltage substitution for the thermocouples; (3) frequency substitution for shaft speeds and flowmeters; and (4) frequency-voltage substitution for accelerometers.

The types of data acquisition and recording systems used during this test period were (1) a multiple-input digital data acquisition system (Microsadic ) scanning each parameter at 40 samples per second and recording on magnetic tape; (2) single-input, continuous-recording FM systems recording on magnetic tape; (3) photographically recording galvanometer oscillographs; (4) direct-inking, null-balance potentiometer- type X-Y plotters and strip charts; and (5) optical data recorders. Appli- cable systems were calibrated before each test (atmospheric and altitude calibrations). Television cameras, in conjunction with video tape recorders, were used to provide visual coverage during an engine firing, as well as for replay capability for immediate examination of unexpected events.

2.4 CONTROLS

Control of the J-2 engine, battleship stage, and test cell systems during the terminal countdown was provided from the test cell control room. A facility control logic network was provided to interconnect the engine control system, major stage systems, the engine safety cutoff system, the observer cutoff circuits, and the countdown sequencer. A schematic of the engine start control logic is presented in Fig. 6. The sequence of engine events for a normal start and shutdown is presented in Figs. 7a and b. Two control logics for sequencing the stage prevalves

AEDC-TRi68-238

and recirculation systems with engine start for simulating engine flight start sequences are presented in Figs. 7c and d.

SECTION III PROCEDURE

Preoperational procedures were begun several hours before the test period. All consumable storage systems were replenished, and engine inspections, leak checks, and" drying procedures were conducted. Pro- pellant tank pressurants and engine pneumatic and purge gas samples were taken to ensure that specification requirements were met. Chemi- cal analysis of propellants was provided by the propellant suppliers. Facility sequence, engine sequence, and engine abort checks were conducted within a 24-hr time period before an engine firing to verify the proper sequence of events. Facility and engine sequence checks consisted of verifying the timing of valves'and events to be within specified limits; the abort checks consisted of electrically simulating engine mal- functions to verify the occurrence of an automatic engine cutoff signal. A final engine sequence check was conducted immediately preceding the test'period.

Oxidizer dome, gasgenerator oxidizer injector, and thrust chamber jacket purges were initiated before evacuating the test cell. After completion of instrumentation calibrations at atmospheric conditions, the test cell was evacuated to approximately 0. 5 psia with the exhaust machinery, and instrumentation calibrations at altitude conditions were conducted. Immediately before loading propellants on board the vehicle, the cell and exhaust-ducting atmosphere was inerted. At this same time, the cell nitrogen purge was initiated for the duration of the test period, except for the engine firing. The vehicle propellant tanks were then loaded, and the remainder of the terminal countdown was conducted. Temperature conditioning of the various engine components was accomplished as required, using the facility-supplied engine component conditioning system. Engine components which required temperature conditioning were the thrust chamber, the crossover duct, start tank discharge valve (test 05 only), and main oxidizer valve second-stage actuator. Table V presents the engine purges and thermal conditioning operations during the terminal countdown and immediately following the engine firing.

AEDC-TR-68-238

SECTION IV RESULTS AND DISCUSSION

4.1 TEST SUMMARY

Fourteen firings of the Rocketdyne J-2 rocket engine (J-2036-1) were conducted on July 23 and 31 and August 8 and 15, 1968, during test periods J4-1901-03 through J4-1901-06. These firings were in support of the S-II/S-V and S-IVB/S-V J-2 engine application and flight support testing. Testing was accomplished at pressure altitudes ranging from 78, 000 to 110, 000 ft at engine start.

Test requirements and specific test results are summarized in Table VI. Start and shutdown transient operating times for selected engine valves are presented in Table VII. Figure 8 shows engine start conditions for pump inlets and start and helium tanks. The total firing duration for the four test periods was 223. 2 sec. Calculated engine performance for the five 32. 5-sec duration firings is presented in Table VIII. Methods of calculations shown are presented in Appendix IV. Specific test objectives and a brief summary of each firing are presented below.

Firing

03A

03B

03C

Test Objectives

Simulate S-IVB first burn to evaluate augmented spark igniter ignition character- istics.

Simulate S-IVB 80-min restart with maximum start tank energy and low fuel pump inlet pressure.

Simulate S-IVB first burn to evaluate maximum gas generator outlet temperature first peak.

Results

Augmented spark igniter ignition was detected at to + 0. 222 sec. Thrust chamber ignition occurred at to + 0. 979 sec.

Thrust chamber ignition occurred at to + 0. 961 sec, and thrust chamber pressure reached 550 psia at to + 1.993 sec. Gas generator outlet temperature first peak was 1750°F with a second peak of 1930°F.

Gas generator outlet temperature first peak was 1640°F.

AEDC-TR-68-238

Firing Test Objectives

03D Repeat firing 03B with start tank gas 50°F colder. .

04A Simulate S-IVB first burn to' evaluate engine start transient with maximum start tank energy and warmest thrust chamber.

04B Simulate S-IVB 80-min restart to evaluate gas generator outlet temperature transient with minimum start tank temperature.

04C Simulate S -IVB first burn to evaluate augmented spark igniter ignition and gas generator outlet temperature transient with maximum start tank energy and propellant pump inlet pressures.

04D Simulate S-IVB 80-min restart to evaluate augmented spark igniter ignition and gas generator outlet temperature transient with maximum starting energy.

05A Simulate S-II firing to evaluate augmented spark igniter ignition with minimum augmented spark igniter mixture ratio, maximum fuel pump inlet pressure, and warmest thrust chamber.

Results

Thrust chamber ignition occurred at to + 0. 939 sec. Gas generator outlet temperature first peak was 2000°F with a second peak of 2190°F. Firing was terminated at to + 1.264 sec by engine safety cutoff system.

Thrust chamber ignition occurred at to + 0. 962 sec, and thrust chamber pressure reached 550 psia at tQ + 1.821 sec. Gas generator outlet temperature first peak was 1870°F.

Gas generator outlet temperature first peak was 1940°F, and the second peak was 2120°F.

Augmented spark igniter ignition was detected 0. 210 sec after engine start. Gas generator outlet temperature first peak was 1960°F.

Augmented spark igniter ignition was detected 0. 260 sec after engine start. Gas generator outlet temperature first peak was 2010°F, and the second peak was 2160°F.

There was no indication of augmented spark igniter ignition before main-stage control solenoid "on" command, at which time the firing was terminated by the engine logic.

AEDC-TR-68-238

Firing Test Objectives

06A Simulate S-IVB 6-hr restart to evaluate engine start character- istics with minimum starting energy.

06B Simulate S-IVB 80-min restart to evaluate gas generator outlet temperature transient with minimum start tank temperature.

06C Simulate S-IVB first burn to evaluate engine start character- istics with minimum starting energy.

06D Simulate S-IVB 80-min restart to evaluate gas generator outlet temperature transient with minimum start tank and thrust chamber temperature.

06E Determine the effect of a -200°F oxidizer injector dome on start transient combustion stability with starting conditions similar to firing 06A.

Results

Thrust chamber ignition occurred at tg + 1. 091 sec, and thrust chamber pressure reached 550 psia at tn-+ 3.233 sec. Gas generator outlet temperature first, peak was 1450°F.

Gas generator outlet temperature first peak was 1730°FJ

and the second peak was 1760°F.

Thrust chamber ignition occurred at to + 1. 062 sec, and thrust chamber pressure reached 550 psia at t0 + 2.124 sec. Gas generator outlet temperature first peak was 2020°F.

Gas generator outlet temperature first peak was 1930°F. There was no second peak.

Total vibration safety counts duration was less than 10 msec before engine cutoff command.

4.2 TEST RESULTS

4.2.1 Firing J4-1901-03A . .

The programmed 32.5-sec duration firing was successfully accomplished. Test conditions at engine start are presented in Table VI. Thermal conditioning histories of various engine components are shown in Fig. 9. Start and shutdown transient operating times of selected engine valves are presented in Table VII. Engine start and shutdown, transients are shown in Fig. 10. Fuel pump start transient performance

10

AEDC-TR-68-238

is shown in Fig. 11. Pressure altitude at engine start was 100, 000 ft. Engine ambient and combustion chamber pressure histories are shown in Fig. 12.

Test conditions were selected to simulate an S-IVB first burn. Aug- mented spark igniter ignition was detected at to + 0. 222 sec. Thrust chamber ignition (chamber pressure attains 100 psia) occurred at tQ + 0. 979 sec, and chamber pressure reached 550 psia at to + 1.-848 sec. Engine vibration in excess of 150 g occurred for 20 msec beginning at tQ +..0. 978 sec. Gas generator outlet temperature first peak was 1560°F with no second peak.

4.2.2 Firing J4-1901-03B

The programmed 7. 5-sec duration firing was successfully accomplished. Test conditions at engine start are presented in Table VI. Thermal conditioning histories of various engine components are shown in Fig. 13. Start and shutdown transient operating times of selected engine valves are presented in Table VII. Engine start and shutdown transients are shown in Fig. 14. Fuel pump start transient performance is shown in Fig. 15. Pressure altitude at engine start was 106,000 ft. Engine ambient and combustion chamber pressure histories are shown in Fig. 16.

Test conditions were selected to simulate an S-IVB 80-min restart with maximum start tank energy.. Augmented spark igniter ignition was detected 0. 248 sec after engine start. Thrust chamber ignition occurred at tQ + 0. 961 sec, and chamber pressure reached 550 psia at to + 1. 993 sec. Engine vibration in excess of 150 g occurred for 6 msec beginning at tQ + 0. 960 sec. Gas generator outlet temperature first peak was 1750°F with a second peak of 1930°F.

4.2.3 Firing J4-1901-03C

The programmed 32. 5-sec duration firing was successfully accomplished. Test conditions at engine start are presented in Table VI. Thermal conditioning histories of various .engine components are shown in Fig. 17. Start and shutdown transient operating times of selected engine valves are presented in Table VII. Engine start and shutdown transients are shown in Fig. 18. Fuel pump start transient performance is shown in Fig. 19. Pressure altitude at engine start was 106, 000 ft. Engine ambient and combustion chamber pressure histories are shown in Fig. 20.

11

AEDC-TR-68-238

Test conditions were selected to simulate an S-IVB first burn with a worst-case gas generator outlet temperature first peak. Augmented spark igniter ignition was detected 0.162 sec after engine start. Thrust chamber ignition occurred at tg + 1. 073 sec, and chamber pressure reached 550 psia at to + 1.951 sec. Engine vibration in excess of 150 g occurred for 35 msec beginning at to + 0. 964 sec. Gas generator outlet temperature first peak was 1640°F with no second peak.

4.2.4 Firing J4-1901-03D

The programmed 7. 5-sec duration firing was terminated at tQ + 1. 264 sec by the engine safety cutoff system because of excessive gas generator outlet temperature. Test conditions at engine start are presented in Table VI. Thermal conditioning histories of various engine components are shown in Fig. 21. Start and shutdown transient operating times of selecfed engine valves are presented in Table VII. Engine start and shutdown transients are shown in Fig. 22. Fuel pump start transient performance is shown in Fig. 23. ' Pressure altitude at engine start was 104, 000 ft. Engine ambient and combustion chamber pressure histories are shown in Fig. 24.

Test conditions were selected to repeat firing 03B with start tank gas 50°F colder. Augmented spark igniter ignition was detected 0. 212 sec after engine start. Thrust chamber ignition occurred at1

to + 0. 939 sec. Engine vibration in excess of 150 g occurred for 5 msec beginning at to + 0.945 sec. Gas generator outlet temperature first peak was 2000CF with a second peak of 2190°F.

4.2.5 Firing J4-1901-04A

The programmed 32. 5-sec duration firing was terminated at tQ + 25. 02 sec by the inadvertent opening (resulting from incorrect procedure) of the thrust chamber purge valve. Test conditions at engine start are presented in Table VI. Thermal conditioning histories of various engine components are shown in Fig. 25. Start and shutdown transient operating times of selected engine valves are presented in Table VII. Engine start and shutdown transients are shown in Fig. 26. Fuel pump start transient performance is shown in Fig. 27. Pressure altitude at engine' start was 78, 000 ft.- Engine ambient and combustion chamber pressure histories are shown in Fig. 28.

Test conditions were selected to simulate an S-IVB first burn with maximum start tank energy and the warmest expected thrust chamber. Augmented spark igniter ignition was detected 0. 243 sec after engine start. Thrust chamber ignition occurred at to + 0.962 sec, and chamber

12

AEDC-TR-68-238

pressure reached 550 psia at tg + 1. 821 sec. Engine vibration in excess of 150 g occurred for 5 msec beginning at to + 0. 978 sec. Gas generator outlet temperature first peak was 1870CF with a second peak of 1750°F.

4.2:6 Firing J4-1901-04B

The programmed 7. 5-sec duration firing was successfully accomplished. Test conditions at engine start are presented in Table VI. Thermal conditioning histories of various engine components are shown in Fig. 29. Start and shutdown transient operating times of selected engine valves are presented in Table VII. Engine start and shutdown transients are shown in Fig. 30. Fuel pump start transient performance is shown in Fig. 31. Pressure altitude at engine start was 100, 000 ft. Engine ambient and combustion chamber pressure histories are shown in Fig. 32.

Test conditions were selected to simulate an S-IVB 80-min restart with minimum start tank temperature. Augmented spark igniter ignition was detected 0.180 sec after engine start. Thrust chamber ignition occurred at to + 0. 945 sec, and chamber pressure reached 550 psia at tQ + 2. 005 sec. Engine vibration in excess of 150 g occurred for 15 msec beginning at tg + 1. 046 sec. Gas generator outlet temperature first peak was 1940°F with a second peak of 2120°F.

4.2.7 Firing J4-1901-04C

The programmed 32.5-sec duration firing was successfully accomplished. Test conditions at engine start are presented in Table VI. . Thermal conditioning histories of various engine components are shown in Fig. 33. Start and shutdown transient operating times of selected engine valves are presented in Table VII. Engine start and shutdown transients are shown in Fig. 34. Fuel pump start transient performance is shown in Fig. 35. Pressure altitude at engine start was 100, 000 ft. Engine ambient and combustion chamber pressure histories are shown in Fig. 36.

Test conditions were selected to simulate an S-IVB first burn with maximum starting energy and maximum propellant pump inlet pressures. Augmented spark igniter ignition was detected 0. 210 sec after engine start. Thrust chamber ignition occurred at to + 0.958 sec, and chamber pressure reached 550 psia at to + 1. 807 sec. Engine vibration in excess of 150 g occurred for 26 msec beginning at to + 0. 956 sec. Gas generator outlet temperature first peak was 1960°F with no second peak.

13

AEDC-TR-68-238

4.2.8 Firing J4-1901-04D i

The programmed 2. 0-sec duration firing was successfully accomplished. Test conditions at engine start are presented in Table VI. Thermal conditioning histories of various engine components are shown in Fig. 37. Start and shutdown transient operating times of selected engine valves are presented in Table VII. Engine start and shutdown transients are shown in Fig. 38. Fuel pump start transient performance is shown in Fig. 39. Pressure altitude at engine start was 100, 000 ft. Engine ambient and combustion chamber pressure histories are shown in Fig. 40.

Test conditions were selected to simulate an S-IVB 80-min restart with maximum starting energy. Augmented spark igniter ignition was detected 0. 260 sec after engine start. Thrust chamber ignition occurred at to + 0. 948 sec, and chamber pressure reached 550 psia at tQ + 1. 984 sec. Engine vibration in excess of 150 g occurred for 9 msec beginning at to + 0. 948 sec. Gas generator outlet temperature first peak was 2010°F with a second peak of 2160°F.

4.2.9 Firing J4-1901-05A

The programmed 32. 5-sec duration firing was terminated at to + 0. 448 sec (main-stage command) by the engine logic because augmented spark igniter ignition had not been detected. Test conditions at engine start are presented in Table VI. Thermal conditioning histories of various engine components are shown in Fig. 41. Start and shutdown transient operating times of selected engine valves are presented in Table VII. Engine start and shutdown transients are shown in Fig. 42. Pressure altitude at engine start was 104, 000 ft. Engine ambient and combustion chamber pressure histories are shown in Fig. 43.

Test conditions were selected to simulate an S-II firing with minimum augmented spark igniter mixture ratio, maximum fuel pump inlet pressure, and warmest expected thrust chamber.

4.2.10 Firing J4-1901-06A

The programmed 32. 5-sec duration firing was successfully accomplished. Test conditions at engine start are presented in Table VI. Thermal conditioning histories of various engine components are shown in Fig. 44. Start and shutdown transient operating times of selected engine valves are presented in Table VII. Engine start and shutdown transients are shown in Fig. 45. Fuel pump start transient performance is shown in Fig. 46. Pressure altitude at engine start was 89,000 ft.

14

AEDC-TR-68-238

Engine ambient and combustion chamber pressure histories are shown in Fig. 47.

Test conditions were selected to simulate an S-IVB 6-hr orbital coast restart with minimum starting energy. Augmented spark igniter ignition was detected 0. 362 sec after engine start. Thrust chamber ignition occurred at to + 1. 091 sec, and chamber pressure reached 550 psia at to + 3. 233 sec. Engine vibration in excess of 150 g occurred for 75 msec beginning at to + 1. 054 sec. Gas generator outlet temperature first peak was 1450°F with no second peak.

4.2.11 Firing J4-1901-06B

The programmed 7.5-sec duration firing was successfully accomplished. Test conditions at engine start are presented in Table VI. Thermal conditioning histories of various engine components are shown in Fig. 48. Start and shutdown transient operating times of selected engine valves are presented in Table VII. Engine start and shutdown transients are shown in Fig. 49. Fuel pump start transient performance is shown in Fig. 50. Pressure altitude at engine start was 99, 000 ft. Engine ambient and combustion chamber pressure histories are shown in Fig. 51.

Test conditions were selected to simulate an S-IVB 80-min restart with minimum start tank temperature. Augmented spark igniter ignition was detected 0.235 sec after engine start. Thrust chamber ignition occurred at to + 0. 953 sec, and chamber pressure reached 550 psia at to + 2. 013 sec. Engine vibration in excess of 150 g occurred for 21 msec beginning at tQ + 0.950 sec. Gas generator outlet temperature first peak was 1730°F with a second peak of 1760°F.

4.2.12 Firing J4-1901-06C

, The programmed 32. 5-sec duration firing was successfully accomplished. Test conditions at engine start are presented in Table VI. Thermal conditioning histories of various engine components are shown in Fig. 52. Start and shutdown transient operating times of selected engine valves are presented in Table VII. Engine start and shutdown transients are shown in Fig. 53. Fuel pump start transient performance is- shown in Fig. 54. Pressure altitude at engine start was 103, 000 ft. Engine ambient and combustion chamber pressure histories are shown in Fig. 55.

Test conditions were selected to simulate an S-IVB first burn with minimum starting energy. Augmented spark igniter ignition was

15

AEDC-TR-68-238

detected 0. 242 sec after engine start. Thrust chamber ignition occurred at to + 1. 062 sec, and chamber pressure reached 550 psia at tg + -2. :124 sec. Engine vibration in excess of 150 g occurred for 33 msec beginning at tg + 1. 052 sec. Gas generator outlet temperature first peak was 2020°F with no second peak.

4.2.13 Firing J4-1901-06D

The programmed 7. 5-sec duration firing was successfully accomplished. Test conditions at engine start are presented in Table VI. Thermal conditioning histories of various engine components are shown in Fig. 56. Start and shutdown transient operating times of selected engine valves are presented in Table VIII. Engine start and shutdown transients are shown in Fig. 57. Fuel pump start transient performance is shown in Fig. 58. Pressure altitude at engine start was 103, 000 ft. Engine ambient and combustion chamber pressure histories are shown in Fig. 59.

Test conditions were selected to simulate an S-IVB 80-min restart with minimum start tank temperature and coldest thrust chamber. Augmented spark igniter ignition was detected 0. 212 sec after engine start. Thrust chamber ignition occurred at to + 0.972 sec, and chamber pressure reached 550 psia at to + 2. 090 sec. Engine vibration in excess of 150 g occurred for 25 msec beginning at to + 0. 960 sec. Gas generator outlet temperature first peak was 1930°F with no second peak.

i

4.2.14 Firing J4-1901-06E

The programmed 1. 25-sec duration firing was successfully accomplished. Test conditions at engine start are presented in Table VI. Thermal conditioning histories of various engine components are shown in Fig. 60. Start and shutdown transient operating times of selected engine valves are presented in Table VII. Engine start and shutdown transients are shown in Fig. 61. Fuel pump start transient performance is shown in Fig. 62. Pressure altitude at engine start was 110, 000 ft. Engine ambient and combustion chamber pressure histories are shown in Fig. 63.

Test conditions were selected to permit a determination of the effect of a -200°F oxidizer injector dome on start transient combustion stability with start conditions similar to firing 06A. Augmented spark igniter ignition was detected 0. 237 sec after engine start, and thrust chamber ignition occurred at to + 1. 093 sec. Total duration of engine vibration in excess of 150 g was less than 10 msec before cutoff command. Gas generator outlet temperature first peak was 1840°F with no second peak.

16

AEDC-TR-68-238

4.3 POST-TEST INSPECTION

The augmented spark igniter assembly was replaced following test 05 because of excessive seal leakage at the augmented spark igniter-to-injector interface. No other engine component damage was incurred during test periods J4-1901-03 through J4-1901-06.

SECTION V

SUMMARY OF RESULTS

The results of testing the J-2 rocket engine in Test Cell J-4 during test periods J4-1901-03 through J4-1901 -06 between July 23 and August 15, 1968, are summarized as follows:

1. All primary objectives were satisfactorily accomplished.

2. Augmented spark igniter ignition was not detected before main- stage signal under conditions simulating an S-II start at minimum augmented spark igniter mixture ratio.

3. An oxidizer injector dome temperature of -200°F had no detectable effect on start transient combustion stability.

4. Except for a leaking seal at the augmented spark igniter-to- injector interface, no engine component damage was incurred.

REFERENCES

Dubin, M., Sissenwine, N., and Wexler, H. U. S. Standard Atmosphere, 1962. December 1962.

2. Counts, H. J., Jr., and Kunz, C. H. "Altitude Developmental and Flight Support Testing of the J-2.Rocket Engine in Propul- sion Engine Test Cell (J-4) (Tests J4-1801-42 through J4-1901-02)." AEDC-TR-68-223, November 1968.

3. "J-2 Rocket Engine, Technical Manual Engine Data. " R-3825-1, August 1965.

4. Test Facilities Handbook (7th Edition). "Large Rocket Facility, Vol. 3. " Arnold Engineering Development Center, July 1968.

17

AEDC-TR-68-238

APPENDIXES

I. ILLUSTRATIONS II. TABLES

III. INSTRUMENTATION IV. METHOD OF CALCULATION (PERFORMANCE PROGRAM)

19

to

■ A I D CH 66-842LJ

Fig. 1 Test Cell J-4 Complex

> m O O ■ H 50 • 00 ro

AEDC-TR-68-238

Fig. 2 Test Cell J-4, Artist's Conception

22

Oxidizer Inlet Duct-

CO 00

Fuel Inlet Duct

Fuel Turbopump Start Tank Discharge Valve

Main Fuel Valve

Turbine Bypass Duct

Oxidizer Turbine Bypass Valve

Oxidizer Turbopump

Auxiliary Flight Instrumentation Package

Exhaust Manifold

Start Tank

Inlet Duct

Pneumatic Control Package

Heat

Fuel Bleed Valve

High Pressure Fuel Duct

Electrical Control Package

Primary Flight Instrumentation Package

> m o n

Fig. 3 Engine Details

To Fuel Flare Stack Fuel Tank Picssurizalion

Fuel Fill and Drain Line

CO

> m o n i H TO

Ov oo f »o u

E 3 Combustion Products ■ Liquid Hydrogen

nil] Gaseous Hydrogen

■xxxi Liquid Oxygen IWWVI Gaseous Oxygen

Pn Gaseous Helium

Oxidizer Tank Pressurization

Oxidizer Fill and Dump Line

Oxidizer Turbopump

Main Oxidizer Valve

Oxidizer Tank Repressurization Line

Fuel Recirculation Valve

Gas Generator

Fuel Bleed Valve

Fuel Turbopump


Fig. 4 S-IVB Battleship Stage J-2 Engine Schematic

AEDC-TR-68-238

Time Index Lines, 1-sec Intervals

1 1 f He Control, Start Tank Discharge Delay Timer, ASI and GG Sparks on Ignition- Phase Control Solenoid Energized

Engine Start

Bleed Valves Close Oxldizer Dome and GG Oxidizer Purge Flow

Main Fuel and ASI Propellant Flow Fuel Temperature OK Signal^

Ignition-Phase Timer Ener- gized 0.450 ± 0.030 sec

Pump Buildup

Ignition-Phase Timer Expires Main-Stage Signal

Purge Control Valve Closed

Main Oxidizer Flow

GG Propellant Flow

Oxidizer Turbine Bypass Valve Closed Main-Stage OK Signal

ASI and GG Sparks De-Energized

□ Main Fuel Valve Open aASI Oxidizer Valve Open

▼ ASI Ignition Detected

«/Start Tank Discharge Delay Timer Expires STDV Delay 0.640 ± 0.030 sec

o STDV Open .Ghg Flow

■ Bypass Flow through Normally Open Oxidizer Turbine Bypass Valve

| I I I I VMain-Stage Control, Solenoid Energized

Spar kB De-Energized, Timer Energized

csSTDV Closed I a MOV Starts to Open

1GC Valves Open

3.30 ± 0.20 sec

iMOV Full Open

90-percent Thrust*/

u. Start Sequence

Signal Time, sec 9 0 1 0 .2 0 3 0 4 0 5 0. 6 O 7 0. 8 0 9 1 .0

Cutoff Signal 1

GG Valve Close (Oxidizer) GG Valve Close (Fuel)

ASI Oxidizer Valve Close

MOV Close

Main Fuel Valve Close

Oxidizer Dome Purge and GG Oxidizer Purge on

He Control Solenoid De-Energizes

Bleed Valves Open

t

D

-

t

CD

r 1 1

b

i

<

b. Shutdown Sequence

Fig. 7 Engine Start and Shutdown Sequence

27

AEDC-TR-68-238


Fire Command A

Prevalves Open Signal 1 r

Recirculation Pumps Off Signal

1 '

Recirculation Valves Close Signal

11

Engine Start Signal \ 1

Start Tank Discharge Valve Open Signal

2

\

3

f Nominal Occurrence Time (Function of Prevalves Opening Time)

20ne-sec Fuel Lead (S-II/S-V and S-IVB/S-IB) JEight-sec Fuel Lead (S-IVB/S-V and S-IB Orbital Restart)

c. "Normal" Start Sequence


Fire Command

Prevalves Open Signal

Engine Start Signal

Oxidizer Recirculation Pump Off Signal

Fuel Recirculation Pump Off Signal

Recirculation Valves Close Signal

Start Tank Discharge Valve Open Signal I

Three-sec Fuel Lead (S-IVB/S-V First Burn)

d. "Auxiliary" Start Sequence

Fig. 7 Concluded

28

AEDC-TR-68-238

-270

LUT

s Q.

-280 -

-290

-300

SYM FIRING

A 03A, 06A, 06C "0 03B

SATURATION- LINE -v

" o 03C, 04B, 06B" . A mn ML rvin V ^

■*-*'

.7 04C, 04[ ) J r

.1 1 START 1 1 TARGET

^SAFE STAR! ENVELOPE -

/ 03B 03C 03D 04A 04B 04C 04D 06B 06D

\ # 03 A i J

IDÄÜ _05

06 A ) j ^ 4 Ul L~— *{- !tg ©

06C\_ 06E7-

30 40 PRESSURE, PSIA

a. Oxidizer Pump Inlet

50

40 PRESSURE, PSIA

b. Fuel Pump Inlet

Fig. 8 Engine Start Conditions for the Pump Inlets, Start Tank, and Helium Tank

29

AEDC-TR-68-238

-100 ECN0ENRGTYUNE-^2700 *» 2900 300°

< 0£

1000

2.5 LB,

CALCULATED FROM CONSTANT "TABLE OF THERMAL MASSLINE PROPERTIES OF GASES",

04B iSApE START- NATIONAL BUREAU OF

'.-ENVELOPE _ STANDARDS CIRCULAR 564, NOVEMBER 1963.

1200 130 PRESSURE, PSIA

c. Start Tank

100

£ '200 s

-300

1

ft V o

£ ,i [T B o

P A A 9 " V

-b Ss-PR ESSU /

RE RANGE FOR EIS i i

GINESTAR i

T^

1 1 | 1600 2000 2400 2800

PRESSURE, PSIA 3200 3600

d. Helium Tank

Fig. 8 Concluded

30

AEDC-TR-68-238

100

= -100

-200

CONDITIONING TARGET -15P±50°F-

—

-40 -30 -10 -20

TIME. MIN

a. Main Oxidiior Valve Second-Stage Actuator, TSOVC-1

200

100

2 o

-100

-200

1 1

CONDITIONING TARGET, 50+.^°F \

! TFTD-4K. TFTD-3-K \ A

TFTD-2I-' -f START

OK IDItSRIUKBINt-j

^/ _ / ^TFTD-8 TFTD- ,J

•"""a If r\ FUEL TURB1NE T? '* w) (%.

mv-i^^ 5?/// *^* CROSS OVERD mJ

1 -2« -20 -16 -12 -8

TIME. MIN

b. Crossover Duct, TFTD 100

B -loo i

-200

-300

COND ITIONir IG TARG ET,-80 ♦ML -

\ "\ *

-211 -20 -16 -12 -8 -i| 0

TIME. MIN

c. Thrust Chamber Throat, TTC-1P

Fig. 9 Thermal Conditioning History of Engine Components, Firing 03A

31

AEDC-TR-68-238

3:

Q_ in

24

20

16

12

8

4 ■■

14UU

1200

1000

800

600

400

200

0

FUELPU MPS PEED, NFP-1P-

-INJ ECTO IE, PFJ-1A CD /

PRESSUF

>

in in /FUEL PUMP ^

' Dl SCHARGE1

IESSURE, Dn-9_

^- COMBUST ION CHAMBER

PF '/>

PK tüUKt, fü-J

\ ̂ J ^

<-— -Jj ̂ /

-.——

1 2

TIME. SEC

a. Thrust Chamber Fuel System, Start

10T IOOO

o

x

OC

in

a.

8 -

6- in

OC 3

800

600

£ 4 £ 400 □c

200

01

1 1 1 OXIDIZER PIIMP

1 DlSCh ARGE PRESSUR E, PO PD-1 >—^

«•*- ■"■

0X1 SPE

MZEF D, N

PUN DP-1

p: PA

M :OMB ISTK INCH AMB ER F 'RESSURE, PC-3

1 2

TIME. SEC

b. Thrust Chamber Oxidizer System, Start

Fig. 10 Engine Transient Operation, Firing 03A

32

AEDC-TR-68-238

24

S 20 ■■

s in a. Ib a. a. ^

m LLI o cz LU 12 ID Q. in 1/1 LU

a. Q s: 8 =j 0-

4

0

o

EC

UJ Q- 1/1

3 0-

moo

\ V 1200 \\ ^FUEL PUMP SPEED, NFP-1P

1000 \

\

800 \\ \

V \ 600 \ n. K— 1 MJEC OR PRESSURE, PFJ-

1 1 1 IA

I n 400 I r^

—run. rureir ui^nrtnut PRFSSIIDF PFPn-?

1 1 1 200

ENGINE /»irrncc 1 ^'

COMBUSTION CHAMBER ODCCCIIDC Dr.3

SI pNAI —■»] 'UI\L. r w

.

0 3

=■*» _

2 3 3 34 35

TIME. 5EC

c. Thrust Chamber Fuel System, Shutdown

10T 1000 T

8

4

2

tn

<n UJ DC

800

600

400

200

TIME. SEC

d. Thrust Chamber Oxidizer System, Shutdown

Fig. 10 Continued

33

AEDC-TR-68-238

ED

o Q_

!00

80

60

40

20

0

800

700

600

2 500 in

J 400 a ID

E 300 Q.

200

100

0

t\ -ox DIZER INJECTOR \ PR •SSURE, P0JGG-2

\ r UEL NJECTOR / \ \ PRESSURE. PFJGG-2

\ \ \ \ -"- \ r v v i \ Ä \ A1

-MA N OXIDIZER VALVE. / POSITION. L0VT

1 / 1 0 1 2

TIME. SEC

e. Gas Generator Injector Pressures and Main Oxidizer Valve Position, Start

2800 T

2400 ■■

' 2000

°m 15CC UJ EC

? 1200 (X QC LU

£ 800 UJ ►—

40C

of

-400

800

700

600

2 500 in a.

uJ 400

in E2 300 a.

200

100

pTE MPER ATUR E, TGG0-1A AN )2

N '"

1 i r

\ i \ / \ / \ / ) / ^C HAMBER PI IESS JRE, PCGG-2 v /

V j

\ n ^—■•

1 V J 1 0 ' 1 '2

TIME. SEC

f. Gas Generator Chamber Pressure and Temperature, Start

Fig. 10 Continued

34

AEDCTR-68-238

a.

CO a.

ÖUU' \

700 \

600 \ \

500 \ \ DIZER IN. ECTOR T ~ux

400 \ PR ESSURE. P0JGG-2

I 300 \ V 200 1 N s

.

100 ENGINE, 1 CUTOFF s J

-FUE PDI

J. INJtUUK :SSURE, PFJGG-

i i

o ,

0 3

"SIGNAL^ i ^

rlu c V 2 3 3 34 35

TIME. SEC

g. Gas Generator Injector Pressures, Shutdown

2800 T

2400 ■

2000 •

CO

cr

0_

400

0

-400■■

800

700

600

1600+ ~ 500 Q.

1200 + u 400 CO ID

800+ § 300 CO a.

l*"»/»-

rTEMPERATU RE, TGG0-1A Ah D2

i»— r \l

r

V

'ENG CUTC SIGF«

. •-CHAMB ERPF tESSL IRE, 'CGG-2 NE V *s

IAL- \ v^

200

100

32 33 34

TIME. SEC

h. Gas Generator Chamber Pressure and Temperature, Shutdown

Fig. 10 Concluded

35

35

m i O

<X

40 i—

30 -

20

10

0

NOTE: STALL INCEPTION LINE IS BASED ON TOTAL HEAD RISE ACROSS THE PUMP. THE DATA PLOTTED ARE PUMP DISCHARGE STATIC PRESSURE CONVERTED TO HEAD. UMIM MKL rrcum rm a TO i cm rurc mc INITIAL 3 SEC OF ENGINE TRANSIENT OPERATION.

^^t *

- r^ f^\ \*

4r ■fffe.

f\ <y

yS* ^3

£%^

> m o n H

A.

0 4 6

FLOW. QF-2. GPM X 10"3

8 10

Fig. 11 Fuel Pump Start Transient Performance, Firing 03A

CO

en

UJ cc -Jl if) to UJ cc

cc UJ CO s: a. x

1000 T

800-■

600 -

400

200

0

CO 0.

LÜ CC !3 in en UJ cc

i_>

1.0

0.8

0.6

0.4

0.2

0.0

1 1 PROPELLANT UTILIZATION i VALVE EXC JURSION \_

f -=«— \

— J ^--

— -C HAMBER PRESSUR I PC-3 t

— —

— — —

— — ■■— -

\

v J—

— -

__ r.T ESI CELL PRESSUR E. PA-2 V >=•

1 1

1 —

■

... 4 / r

\ T

Li — —

" —

—

i=-rr -r= r-= i 1

--• — .... — —

--- — — - - \ \

-10 0 10 20 30 40

TIME, SEC

Fig. 12 Engine Ambient and Combustion Chamber Pressure, Firing 03A

> m O n ■ H 70 ■

AEDC-TR-68-238

100

■100

-500

■

CONDITIONING TARGET, -150±5C°F-

1 1 i

""■*

■ 1 " "l .

1 -MO -30 -10 -20

TIME. MIN

a. Main Oxidizer Valve Second-Stage Actuator, TSOVC-1

800

600

400

200

-200

START TANK C3^ FUELTURBINE

TFTD-2

TFTD-8

CROSSOVER DUCT TFTD-3 AND 4

-CONDITIONING TARGET,

.HOt^ASREADON TFTD-3 AND 4 AT

-ENGINE START —

-21 -20 -16 -12 -8

TIME. MIN

b. Crossover Duct, TFTD

100

K

-200

-300

1 |

CONDI TIONIN r i

5 TARGET, 50±50°F—

/ '

—

i ■ -M -20 -16 -12 -fl

TIME, MIN


Fig. 13 Thermal Conditioning History of Engine Components, Firing 03B

38

AEDC-TR-68-238

28

0- 2:

Q_

12"

4-

0 ■■

1400

24•■ 1200

20 ■■ 1000

2- 16 f £ 800

S 600 in UJ

E 400

200

0

i FUEL PUMP S PEED, NFP-1P ^

1

-INJ ECTOR

I s 1 1

y^—.

TUEL PUMP _ / X DISCHARGE i JJytfc COMBUST ION CHAMBER PRESSURE, 'jKjr!

— "PRESSUR E, PC-3

1

1 ■ -

—

1 2

TIME. SEC


10 T 1000

b

31 Q.

LU a. in a. 2: a.

8 ■■

6+ In 600 a.

4-

800

tu

ffi 400 tu cc Q.

2 ■ 200

01

r-OXIDIZER PUMP

\

3i*rw mot ruts I

SURE POP D-1P

\ 1

rOJ \s

(IDIZERPUMP" >EED, NOP-1P

A jf

V P

OMB RESS

JSTIC URE,

NCH PC-3

\MBE \

—i

rVI 1 2

TIME. SEC


Fig. 14 Engine Transient Operation, Firing 03B

39

AEDC-TR-68-238

28

24

2 20--

2: in Q. Ilv O. ct:

. UJ Q a: UJ 12- . ID

a. tn in UJ

cc n n 5: 8 Z3 Q.

1400

1200

1000

800

S00

400

200

1 1

y-fU :L PUMP S PED. NFP-1P

\ \

■ \ 1

■t ̂

^^ -IN.

eiici

ECTOR PR ISSURE, P :J-1A

I »HUB

JISCHARGE PRESSURE, PFPD-2 1 1 1 1 1 1 , \

tNOINt -CUTOFF-

SIGNAL-

—COMBUSTION CHAMBER KKtbbUKE, ?K-5

=SS£äL^^^__

7 € 9 10

TIME. 5EC


m 1 O

CO

Q.

10T

8-

1000

800

a.

in in cc

600

400

200

\WN 'S^— ■^s \

i

\ -ox DIZE IPU APS »EED, N0P-1P

V ^0 XIDI ZERF •UMP 1 1

\ D ISCHARGE PRESSURE, P0PD-2

1 1 1 1 1 1

^( COMBUSTION CHAMB »RESSURE. PC-3

ER

L X

^N

^

8 9

TIME. SEC


Fig. 14 Continued

10

40

AEDC-TR-68-238

o

l_> cc ÜJ CL

en o 0_

800

700

600

100 T - 500 in

80 +

60

40 ■

20

0

iJ 400 cc in S 300 cc

200

100

0

I

**

roR / \ v FUEL INJECTOR ^OXIDIZER INJEC

\ \ PRESSURE, PFJG6-2 rnujuKt, rujbi»-* 7

\ \ / \ S* 1

» -N\A N0XIDIZ ER

/ VALVE POSITION, L0VT

. 1 / 0 1 2

TIME. SEC


2B00

2400

2000

1600-

cr cc ÜJ

£ 800■■ ÜJ t—

400-

-400

in a.

800

700

600

500

1200- ul 400 cc -=> in in uj cc Q.

300

200

100

/-TF MPEF ATUF E TGG0-1A AN 32 r 1 t

/ 1 k J. <\ \ i

r^ \ r^

^^*~~

\ / V ̂ \ / / ^ *-> \ / /

\ / / 1

t / s > V / / N . \ \ u ^-CHAMBER PRESSURE , PCGG-2 v \ ̂ V J

. \ 0 1 2

TIME. SEC


Fig. 14 Continued

41

AEDC-TR-68-238

in ü_

ÜJ QC ID in in UJ DC

ÖUU

700

600 \

>—OXIDIZER INJECTOR

500 V ^-"" PRESSURE, POJGG-2

\

MOO \ \

300 1

I

V 200 \

CMR IMC

100 .CUTOFF _ I SIGNAL- \ ^

-TÜLL injLV>IUR PRFSSIIRF PFIfifi-2

0 1 \ 1 1 ' 1 1 V 7 E J c ) 10

TIME. SEC


28001

CE

m o_

■ LU CC

in in UJ cc 0_

800

700

600

500

400

300

200

100

0

!

24UO-

2000

am 1600- ]

oc 2 1200- cc

/ -TEMPERATURE, TGG0-1A AND 2

/

£ 800- -\ i_ V

*■— — — ÜJ

400- -ENGINE .CUTOFF SIGNAL-

■CHA WER \ PC GG-2 0- I X PRESSUR

A u/

r

-400- ^ 8 g

TIME. SEC


Fig. 14 Concluded

10

42

tn i O

CO

4 6


Fig. 15 Fuel Pump Start Transient Performance, Firing 03B

> m a n i H »

CO Q_

CC LU GO s: cr x

1000 r

800-■ en a.

£ 600 en in

400 -

200 -

0

en

en en LU cc

e_)

1.0

0.8

0.6 —t

0.4

0.2

0.0 -10

; ; i 1 i 1 i ■ i

i

1

i j 1 i l

J.LD L_ I

_\ 1 1 1

1 i | ' : l__ J ..

— I 1

CHAMBER PRESSURE, PC-3r 1 _

1

— —

. -.,

! !

-.1- Li ! .'

i

i

I ■■

...

i i

— --

1 rfca.

] i

i 4 J^ - ... ..

i i i 1

■ r1"i ~i'~ / ! ! i ! i 1 /l ! ' 1 I ! i'!i i i i

ill i ■ ; f i i ' : i ' , ill:

i ! TEST CELL /: i s i i ! 1 ! i

i \ 'RESSURE, PA-2-^ KJ : ' 1 ! ■ I'M ! \ \ \ \ ■ ! /x : : ! i i ! : j 1 . ■ • I

i i : ! ^yy^~-—^L/ ! 1 ; l I i | i 1 ! : : ! '

— : :::>:■.

i ; l ; ■ , ! 1 ,

i 1 1 ' i i '' • . ! U i , i i ! i i i ■ j ■ / \ V : ;

-5 0 5

TIME. SEC

10 1-5

> m o n

Fig. 16 Engine Ambient and Combustion Chamber Pressure, Firing 03B

AEDC-TR-68-238.

100

fr 0

i s iu & -100

-200

.

CONDITIONING TARGET. -150 ±50^—

— -40 -30 -10 -20

TIME. HIN

g. Main Oxidizer Valve Second-Stage Actuator, TSOVC-1

200

100

I • -100

-200

ITFTD-4-»

ITFTD-3 ITFTO-J

1FTD- *J SET, 50

^ ■ ICON

OXIDIZERTURBINE-7' 9ITI0NI

-TFTD-I

NGTAR 5W START TANK -V —

FUEL TURBINE -?* ■ A(T^^

I HB-Z-" ;ROSSC WER DU CT-* TFTD-3/ WD 4

-2H -20 -16 8 -12

TIME. HIN

b. Crossover Duct,. TFTD 100

£ -100

-200

-300

*"v ... N

\

\ \ v \ |c MDITIi JNINGT ÄRGET. -250±i 5°F-\ \

\

_\

.

-91 *20 -16 -12 -8 -U 0

TINE. HIN


Fig. 17 Thermal Conditioning History of Engine Components, Firing 03C

45

AEDCTR-68-238

o

Q_ to

Q- s: Q.

28

24

20 +

IS

12--

8-

4-

0

a.

to

a:

1400

1200

1000

800

600

400

200

FU EL PI IMP SPEED. NFP-1P-

/ -INJ ECTOR

/ PRESSURE, PFJ-1A

/ ^

/FIIFI PI IMP

j\ DISCHARGE

f PRESSURE, i l—rnMRiKTinw TMAMRFR

/ PFPD-2 =>v^

PR ESSURE. PC-3

« i-— ■*"

L 2

TIME. SEC


10T IOOO

o

a. a:

in

0- IE

8

S-

4-

B00

</> 600 a.

£ 400 UJ

Q-

2 ■■ 200

01

IRPL RGEF D-1P

iT^\ A A 0XIDIZ DISCHA

MP »RESSURE. POP

r\r-\ AAJ

IDIZ EED,

\ -ox

V sp

ERPU NOP-

IMP IP i

\ :OMB PRES

ER— <— USTION CHAMB SURE, PC-3

: /

1 2

TIME. SEC


Fig. 18 Engine Transient Operation, Firing 03C

46

AEDC-TR-68-238

28 T 1400

24- 1200

2 20- 1000

£ 16+ a! 800 a.

tu Q.

a.

12

8 -

4--

0 ■■

4- = 600 in in

0-

UMP SPEED, N P-1P

FUEL PUMP DISCHARGE PRESSURE, PFPD-2.

INJECTOR PRESSURE, PFJ-1A _| 1 1 1 h COMBUSTION CHAMBER— PRESSURE, PC-3

33 34

TIME. SEC


35

10T IOOO r

8:

in a. 3

8

6- ■ in a.

14

2-

O1

in en tu CO Q.

800

600

400

200

32 33 34

TIME. SEC


Fig. 18 Continued

47

AEDC-TR-68-238

ED

C_) oc

160 T

140 ■

120-

100

m 0-

40 ■

20-

0-

800

700

600

s 5°° OL

80+ UJ* 400 oc

60+ S 300 OC 0.

200

100

0

A \ \ »—i FUEL INJECTOR -OXIDIZER IN ECTOR

\ ^ PRESSURE. PFJGG-2 PR ESSURE. P0JGG-2 >

\ 1

\ \ /

-MAIN OXIDIZER

/ VALVE POSITION, LOVT

_J / 1 0 1 2

TIME. SEC


2800 T

2400-. 700

2000-

°m 1600- UJ oc 2 1200 CC OC UJ

£ 800 UJ t—

400 - ■

0 ■■

-400-

800

600

B 5°° a.

UJ oc

oc a.

400

300

200

100

r TEMPER* *TUR :, TGG0-1A AND 2 .

A \ ,*~— \ t

\ \ \ V \

\ -CHAMBE RPR ESSUI IE, P CGG-2

V \ \ \ ■ ^A-

S

V / i

. , *

0 1 2

TIME. SEC


Fig. 18 Continued

48

AEDC-TR-68-238

800 •

700 \ |\ ^-OXIDIZER INJEC1 roR 600

PRESSURE. POJGG-2

S 5°° UJ* 400 cc v in 52 300 cc

\ v Q_

200 s

- ENGINE- -CUTOFF -

S1GNAL- 100 I

EL INJECT! s +S -Fl 3R

0 3

1 c II!! ~^^

2 3 3 34 35

TIME. SEC


2800 T

2400-

2000-■

a:

cc

400-

0-

-400

800

700

600

1600+ ~ 500 a.

1200 4 UJ* 400 cc -=> £= 800+12 300

cc

200

100 -ENGINE -CUTOFF

SIGNAL

TEMPERATURE

CHAMBER PRESSURE. PCGG-2

TGG0-1A AND 2

32 33 34

TIME. SEC


Fig. 18 Concluded

35

49

40

30 - i o

NOTE: STALL INCEPTION LINE IS BASED ON TOTAL HEAD RISE ACROSS THE PUMP. THE DATA PLOTTED ARE PUMP DISCHARGE STATIC PRESSURE CONVERTED TO HEAD. DATA ARE FROM FM SYSTEM FOR THE INITIAL3 SEC OF ENGINE TRANSIENT OPERATION.

20

o

Q CE 10

0

> m o n

70

4 6


8 10

Fig. 19 Fuel Pump Start Transient Performance, Firing 03C

luuu-

er 800- •—4

co Q-

» LU CO 600- 3 CO co LU oc D_

cc 400- LU CD 2: cr X . C_)

200-

r\-

CO Q_

CO CO LU CC Q_

UJ (_)

1.0

0.8 -

0.6

0.4

0.2

0.0

1 CHAMBER PRESSURE, PC-3-^

1 \

PR0PELLANT UTILIZATION \ VALV 'EEXC URS ION ^ f

**-« j r 1

C LS ELL

/ 1 'RESSURE, PA-2 >

"%M| J

-—,{.

1 \ \ / \

-10 0 10 20 30 40

TIME. SEC Fig. 20 Engine Ambient and Combustion Chamber Pressure, Firing 03C

> m a n

AEDC-TR-68-238

lDO

Jr

i -100

-200

CONDITIONING TARGET, -150±50°F-v

\ k 1 1 1 1 II |

-MO -30 -10 -20

TIME. HIN


0XLDIZER TURBINE -i

START TANK ^ / ; ^-TFTD-8

a a; s

-200

CONDITIONING TARGET, 170 * J5** AS READIX

ON TFTD-3 AND TFTD-4 AT ENGINE START—-^

-24 -20 -16 -12 -8

TIME. HIN


S -100 S

LU t—

-200

-300

[

CON )ITION NGTAR SET, 50 ±50°F- y

-2-1 -20 -16 -12 -8

TIME. HIN


Fig. 21 Thermal Conditioning History of Engine Components, Firing 03D

52

28-1

24-

20

16

12-

8

4

0

d in

■ Q_

UJ cc

. :D en in UJ IE Q.

moo

1200

1000

BOO

600

400

200

AEDC-TR-68-238

-FUEL PUMP SPEED, NFP- LP m O

X

0_

O

LU -FUEL PUMP "■

in > DISCHARGE PRESSURE, PFPD-2 3E

/ -INJECTOR 0-

/ "ZJ>*

-_. V L ' '

/ = UUIV1BU5IIUN LHAMBtK -PRESSURE, PC-3 — ' ' 1 1 A ""-J-«s= u =ENGIN

CUT0F SIGNA

E. SEC

0 [ ) 1 1

TIM

F 2 L

3

a. Thrust Chamber Fuel System, Start and Shutdown

IOT IOOO

a. cc

in

3 Q_

rOXIDIZER PUMP tf DISCHARGE PRESSURE, P0PD-1P

SIGNAL

TIME. SEC

b. Thrust Chamber Oxidizer System, Start and Shutdown

Fig. 22 Engine Transient Operation, Firing 03D

53

AEDC-TR-68-238

800

700

600

IODT ~ 500

400

300

200

100

0

tu OL 0- U 80- ' UJ t— cc z 3 UJ en or 60- . in

UJ LU CL Q. Q_

z" 40- o ■-^ (—

PO- LT1 O 0_

o1

K \ \ rFU EL INJECTOR PRESSURE, PFJGG-2

\ \ ><fr ^-ox DIZER INJ

:SSURE. PI ECTOR

^ / A PR DJGG-2 v I / \ / n V

1 \ L P \ '

1 & 1 / y\ V- -MAIN0XIDIZER

/ \ \ ^"VALVE POSITION, LOVT

0 i I « 3 '-ENGINECUTOFF SIGNAL TIME. SEC

c. Gas Generator Injector Pressures and Main Oxidizer Valve Position, Start and Shutdown

2800 T

2400

2000 -■

16001 ~ _ Q. CC

2 1200 + <x GC

% 800 +

400--

0-

-400-

in en cc

800

700

600

500

400

300

200

100

•-ENGINE CUTOFF SIGNAL TIME. SEC

Gas Generator Chamber Pressure and Temperature, Start and Shutdown

Fig. 22 Concluded

--TE MPER ATURE. TGG0-1A AND 2

r^ K i

\ / \ " 1 / \ / \ / \ / - CHAMBER PR ESSU IE, P CGG-2

v / \ / ,

\ U \

> s^

v

\ / —1 /

54

m i O

01 01

O cr

4 6

FLOW, QF-2. GPM X 10"3

Fig. 23 Fuel Pump Start Transient Performance, Firing 03D

a n

70

CXI OS

en Q_

LÜ CC ID en en LU cc CL

CC LU CQ

d

(_)

1000 T

800--

600 --

400-

200 ■

01

en Q_

LÜ cc en en LU CC CL.

LU e_>

1.0

0.8

0.6

0.4

0.2

0.0

r1— -TESTCE LL PRESSURE, PA-Z

—

—

MB ER JR -CHA PRESS I, PC-3 *

>-— —S-. 1 —

—- —

: —

) s —

^

> m o n I -I TO

-10 -5 0 10 15

TIME. SEC

Fig. 24 Engine Ambient and Combustion Chamber Pressure, Firing 03D

ÄEDC-TR-68-238

100

a" 0

►- s UJ

fc -100

-200

[CONDITIONINGTARGET, -150±50°F ■\

\ ■ \ \

V s ,

-40 -30 -10 -20

TIME. HIN

o. Main Oxidizer Valve Second-Stage Actuator, TSOVC-1

200

CONDITIONING TARGET. 50 !»<*

TFTD-8

CROSSOVER 0UCTJ tTFTl«AND4

-16 -12 -8

TIKE. HIN

b. Crossover .Duct, TFTD 100

5 -100

1 -200

-300

CONDITIONING TARGET, -Sot^T- -sj •v

^! "

-24 -20 -1 -16 -ia -B

TIME. HIN



57

AEDC-TR-68-238

,28

24

UJ a. en

3 a.

en

o LU

Q_

20 -

16-- Ü-

12

4-

CE

to

.. § «n in

14UU

ED, NFP-lP-x 1200

rUtL PUMP bPt

1000 FU PR

IPU1 ESSU

MPD RE, P

SCH FPD-

ARGE r FUEL PRES

NJECTOR

800 2-. 1 SURE, PFJ- ■1A

.> .—

600 *S

400 J

/ CHAN BER PRESSURE,

200 / >C-3

/

0 l*SS5 -h ^"

1 2

TIME, SEC


10T IOOO

8

B -

01

800

rx in 600

4+ £ 400 LU OC Q_

2 ■ 200

1 1 1 f»Yini7FP PUMP ,K \A^ ^A Ais DIS ruAor.r DE ariDn.9

V1- •v

—

0X1 SPE

DIZE ED, N

»PUN OP-1

IP

^-c MME ERP EESS JRE, >C-3

k r

J ■ 7

1 2

TIME. SEC


Fig. 26 Engine Transient Operation, Firing Ü4A

58

AEDC-TR-68-238

281 moo

24- 1200

i O 20- 1000 X cr z (O Q. , lb ■ Q. ÜUU

w UJ o cc UJ LlJ 12 . =3 600 0- tr> 1/1 UJ

8- a.

MOO ^ 0.

4 200

0- 0

— FUEL PUMP . w SPEED,

-^F UEL PUMP DISCHARC »RESSURE, PFPD-2

;E \ NFP-1P -

- y \ \ \

1 / \ \ v

'UEL NJECT0R / / \ \ PRESSURE, PFJ:1A - /

/ } M /

1 \

CHAMBER PRESSURE, PC-: V \ 1

I \

ENGINE CUTOFFS GNA v\ V ^v h-ita *=-"* ™==

23 24 25

TIME. SEC


26

10T 1000

■x.

LJ

in 0-

8-

6

4--

O1

800

rx ? 600

BE

£ 400

2 • 200

c 1 1

XIDIZERPUMPSPEE ■ i ' l - 3, N0P-1P -\

i *

/IP D DPD-;

OX PR ISSURE, P s \

, ^

CHAM JER PRESSURE, PC-3

E^ GINE CUT( FFS GNAL L 23 24 25

TIME. SEC


Fig. 26 Continued

26

59

AEDC-TR-68-238

800

700

600

lnn-i cr son

7 to UJ 0- 0. o 80- ■ tu 400 1— DC z =3 UJ tn

nr 60- en UJ 300

IM cc Q. Q.

2 40- 200 ED ■—•

20- 100 n o_

0- 0

r SAS GENERATOR FUE NJECTOR PRESSURE,

^~Si ' ;

/

/ PFJGG-2

1 \ -GAS GENERATOR \ 0XIDIZER INJECT0

PRESSURE, R A .

\

\ POJ GG-2-j

j J

WAIN 0X1DIZER VALVE

/ Dncmrui in\r

/ 1 1 0 1 2

TIME. SEC

e. Gas Generator Injector Pressure and Main Oxidizer Valve Position, Start

2B00T

2400-■

2000

1600- ~ 500

^ 1200 - az £ BOO

400-

0-

-400-

800

700

500

in in

400

300

200

100

GAS GEN IRAT0R 01 TUET TEMPERATURE, TGG0-1A AND 2-j

N \

\ /

\ /

\ /

\ \ *N^- GAS GENER AT0R CHA MBER v PRESSURE, PCGG-2

\ \

\

0 1 2

TIME, SEC


Fig. 26 Continued

60

AEDC-TR-68-238

800

700

600

S 500 in 0-

UJ

in in LU

400

300

200

100

■ -. -

1 1

GAS GENERATOR OX DIZER INJECTOR PRESSURE, POJGG-2 *\

GAS GENERATOR FUE iMicrrno DDCCCIID !, PFJGG-2

1 I E NGIN E CUTOFF SUJNAL^ \

> V 23 214 25

TIME. SEC


26

2800 T

21100"

2000

1600 -

£ 1200 cz oc a. 2: UJ

800 ■

400 ■

0 •■

-100-

800

700

600

B 5°° Q_

uJ 400

in in cc

300

200

100

■

r GAS( ;FNER ATOR CHA MRFR PRFS SIIR E PCGG-2 f GAS GENERATE R OUTLET TEMPERA! fURE, TGG0-1AAND 2-| 1

T -«1

■\

\

MAL- 1

ENG NEC UTOFF SIG V V- V

\ V 23 24 25 26

TIME. SEC h. Gas Generator Chamber Pressure and Temperature, Shutdown

Fig. 26 Concluded

61

> m o n

m i O

OS N3

I

a (X ÜJ

4 6



1000 T

800-

ÜL

S 600-

ÜJ ac

cc UJ CO

cc

400-

200-

01

a.

UJ cc CD in UJ cc

UJ

1.0

0.8

0.6

0.4

0.2

0.0 -10

1 1 / PROPELLANT UTILIZATION / VALVE EXC URS ION ~\ /

v .... /

\ /] ——

i L f J J s i rr i / ^ CHAMBER PRESSURE, PC-3J

/

1 /

\ i V Z""-« y

j

TEST CELL PRESSURE, PA-2^1

\

/ N 10 20 30 140

TIME, SEC

> m o n

Fig. 28 Engine Ambient and Combustion Chamber Pressure, Firing 04A

AEDC-TR-68-238

100

-100

-200

CONDITIONING TARGET, -1501 50°F

^N "N

-140 -30 -10 -20

TIME. HIN


\St

800

600

400

200

-200

START TANK

FUEL TURBINE

TFTD-2

TFTD-8

CROSSOVER DUCT TFTD-3AND4!

CONDITIONING- TARGET, -

170tj°°F

(AS INDICATED BY TFTD-3 AND 41-

-24 -20 -16 -12

TINE. MIN


8 -N

100

E B -loo cz

-200

-300

1 :ONDIT ONING TARGET, 50±Z Pt'-^

-21 -20 -16 -12 -6 -il 0

TIME. MIN



64

AEDC-TR.68-238

28 T 1400

&

Q. in

z: => Q-

1 2

TIME. SEC


en

Ö

a. in a_ x:

TIME. SEC



65

AEDC-TR-68-238

m Q

3: Q-

LU Q. in

Q_

Q.

28T 1400

24- 1200

20

16

12

8

1

O1

1000

o- 800

S 600 m

400

200

^- FUEL PUMP SPEED, NFP-1P

V^ k

\ V, ̂ ~r »RESSURE, PFPD-2

Jt

V A r

# \ ^

CHA t ̂ ÜBER \

- \ :UEL NJECTOR PRESSURE, PFJ-1A PPFCCIIQ ■ \ r

PC-3 *i

i i

, ̂ — ENGINE CU1 rOFF SIGNAL

8 9

TIME. SEC


10

10T 1000

CC

a

in

Q_

8

6 ■■

4

2 -

01

800

tn 600 Q_

UJ DC =3 CO on LU OC a.

400

200

i i > /-

JXIDIZER PRESSURE

PUMP DI SCHAR POPD-2

GE

<^^y ^•N-l W f S\ V \

\ IN i V* y

1 < jAiuizjirc r.umr SPEED NOP-1P

CHAf PRFS

IABER SURE N \

PC-3 t

\ ^-E gGIN c Pirrrtcc CIPKIAI

■ V/UI

1« X ̂ K ̂ ^

8

TIME. SEC


Fig. 30 Continued

10

66

AEDC-TR-68-238

160T

mo-

120

0_ O

UJ

CC

o CL

U0-

20 ■■

0-

800

700

600

100+ ~ 500 in a.

80+ tu* 400 cc ID

60 4 S 300 DC

200

100

0

_TGAS GENERATOR FUEL INJECTOR, PRESSURE, PFJGG-2

i 4' \ \

UA5 UtNtKAlUK nYIIM7FD ,/

\ UAILMi.LI\ INJECTOR

\ PRESSURE,

\ P0. GG-2—, \

"-MAIN 0X1DIZER VALVE /

or c ITI nu I ra/T rujuiun, LVVI

. 1 / D 1 2

TIME. SEC


2BO0T

2400 ■

2000

1600+ ~ in

cc DC UJ 0. z UJ

1200

B00

«00 ■■

0-

-400-

UJ cc in in UJ- cc a.

800

700

600

500

400

300

200

100

r-GAS GENERATOR OUTLET fEMP ERATL RE, 1 rGG0-lA A ND2

n \ v \ V

< \ /

^^ —J —*. \

i

V ^G KS GENERATOR 1 CHAM BER k \ P »ESS URE, PCGG-2

\ V fis-

V ) . 0 1 2

TIME. SEC


Fig. 30 Continued

67

AEDC-TR-68-238

800

700

\ 600 \

f 5°° \ \ GAS GENERATOR FUEL

uJ 400 V «^ NJECTOR PRESSURE, PFJGG-2"

V tn 12 300 oc

A i s~t iAS GENERATOR 0X1DIZER

NJECTOR PRESSURE, P0JGG-2 V ,/ 1

200 vl r

^] — —

100 I N ̂ ~ ENGINE CUTOFF SIGNAL

n r V 1 8 9

TIME. SEC


ia

2800-r

2400-

2000-■

1600-

1200 ■ =3

CE tc LU £ 800 + LU I—

400

0 ■■

-400-

800

700

600

en in ~ 500

ÜJ ac =3 tn tn LU OC Q_

J-t ;ASG ENER ftTOR CHAMBER A ' F •RESSURE, PCGG-2

/ /

r< 5AS GENERATOR OUTL ET IA AND 2 h TMPERATU RE, TGGO-

\i L \J •'

V ^-ENGIN ECU! OFF SIGNAL

y ̂ 1 S K | ■

400

300

200

100

7 ' 8 9

TIME. SEC


Fig. 30 Concluded

10

68

140

30

OS CO

n i O

X

r-

I u. T.

Q IX

20

10

NOTE: STALL INCEPTION LINE IS BASED ON TOTAL HEAD RISE ACROSS THE PUMP. IHt DAI/» PLUI ItU AKL PUMP DISCHARGE STATIC PRESSURE PHMX/FRTFn TH HFAn HAT A APF

- /

FROM FM SYSTEM FOR THE INITIAL 3 SEC OF ENGINE TRANSIENT 3PERATK )N.

N>

&7

< v€1

hn

%

j

^-

4 6



8 10 > m o r>

-a o

1000T 1-0

BOOt 0.8

(n Q_

CO a. c 600 + - 0.6 in in LU

a: 400 LU GO

cr c_>

(/"> CO LU

8F 0.4

u

200- 0.2

01 0.0

> m a n

1 \

CHAMBER PRESSURE, PC-3 ~\| i

L v .\

1

TEST CELL PRESSURE, PA-2-A

\

\ —3.

' L . ) Ns

-10 -5 10 15

TIME. SEC Fig. 32 Engine Ambient and Combustion Chamber Pressure, Firing 04B

AEDC-TR-68-238

100

S -100

-200

CONDITIONING TARGET. -150±50°F

1 I 1 1

-40 -30 -10 -20

TIME. MIN


e o

-100

-IB -12 -8

TIME. HIN


100

2 -100 £

-200

-300

RGET. -. +20«. |co NDITI0NINGTA

Ns, ,

-

-2U -20 -IB -12 -8 -i| 0

TIME. HIN



71

AEDC-TR-68-238

28

214

16--

12

8

4

O1

a. DC

Q_ en Q_

oc

o UJ UJ Cl- io

0- 3E

14UU

1200

1000

800

600

400

200

n

FUEL 'UMP SPE :D, NFP-1P^

v . / y FU PR

IPU ESSU

MPD RE, P

SCHARGE / >

rFUEL INJECTOR •—1

in FPD- 2 A \ PR ESSURE, P FJ-1A \ .t-

UJ oc —y 10 in oc a.

/ ^ CHAMBER PRESSURE,

/ YKri

/ L 1 2

TIME. SEC


10T 1000

8 -

cr 6+ in 600

4

2-

800

£ 400 UJ oc

200

0X1 DIS

| 1

DIZER PUft CHARGE PF

IP tESS JRE, pnpn ji

^-*J rUrU

_0X SPE

DIZE :ED, v

RPU OP-

VIP PA / y

> / \ / ^-c

p HAMB >3

ERP IESS JRE,

ji / J~

1 2

TIME, SEC



72

AEDC-TR-68-23B

28 T 1400

24 1200

2 20 - 1000

0-

Q-

0_

16+ £ 800

12--

3

4

0-1-

Ü 600 in ÜJ

400

200

,y — FUa PUMP SPEED, NFP-1P

\\ , \- r UEL PUMP DISCHARGE . r \

PRESSURE, PFPD -2 i "

^ ^

\

CHAMRF D \

PRESSU *E, i S- FUEL INJECTOR PRESSURE, PFJ-1A PC ^ 3

^-ENGIN ■CUTOFF SIGNA . #

.

—1 ^ --.. ■ -

32 33 34

TIME. SEC


35

tu a. in

I

TIME. SEC


Fig. 34 Continued

73

AEDC-TR- 68-238

800

700

600

ino-i (X 500

z in LlJ Q_ fl- ea 80- ' LLJ 400 t— DC Z ID LLJ to

60- . in LU 300

LU EC Q_ CL.

• z 40- 200 o t—*

20- 100 o Q_

QJ 0

r GA5 GENERATOR FUEL

/ INJECTOR PRESSURE, DC r.r.-o

/

\ \ GAS GEN SAT0R

\ OXIDIZER INJECTOR PRESSURE,

\ \ truj|ji>-£ ]

/ VI „ K / ^>^ 1

-MA N OXIDIZER / VALVE POSITION, LOVT

/ 0 1 2

TIME, SEC


2800 T

2400-

2000 - -

LU m n

DC _) 1200- ' LU (T oc tr a LU in

800- . in LU

LU CC 1— Q_

400-

0-

-400-

800

700

600

1600 - ~ 500

400

300

200

100

r-GAS GENERATOR OUTLET

1 TE MPEF iATURE. TGG0-1A AN D2

rt \ \ \ \ \

j JERA1 ER PR

Gf S GE UK

/ CH IAMB ESSU RE. PCGG-2

\ -

0 1 .2

TIME, SEC


Fig. 34 Continued

74

AEDC-TR-68-238

tn a.

in in LlJ DC 0-

ÜUU Ü !■ i ""' *

700 L - GAS GENERA! OROXIDIZER

600 \ INJECTOR PRESSURE. P0JGG-2~

\ 1

500 \ 1 -\ ASGENERATOR FUEL * \ i

400 \ INJEC1 rOR PRESSURE. PFJGG-2

300

200 cKin Mr _i

100 CUTOFF SIGNAL-

I « N

0 ^ 32 33 . 34

TIME. SEC


35

2800-f

2400 ■ ■

2000 ■■

° 1600- 2 • in

2 1200- ÜJ a or tu £ BOO- UJ I—

400-■

0-

-400-

in in tu cc

800

700

600

500

400

300

200

100

■32 33 34

TIME. SEC

h. Gas Generotor Chamber Pressure and Temperature, Shutdown

Fig. 34' Concluded

1 1 1 ^GAS GENERATOR CHAMBER.

P RESS JRE, PCGG-2

* r-GAS GEh ERATOR 0 UTLET

TEMPERATUR I. TGG0-1A AND 2

j \ /

\ll *

V •

- FMfi INF 1

.CUTOFF I SIGNAL- N„ N

| -=»

V ■

35

75

m i O

cr

m o n

4 6

FLOW, QF-2, GPM X 10"3


-a

1000T I.O

800- 0.8

£ 600 ID in en UJ DC

rr 400 UJ CO

(X X (_)

en Cu

UJ oc ID- in in UJ az

i_>

0.6

0.4

200- 0.2

01 0.0

I I -PR0PELLANT UTILIZATION

VALVE EXCURSION

—^_ r 1AME *- -a tR PR ESSURE, PC-3

-TES' C /■ ELL PR ESSURE, Vk-L

/

d r

) . F

—^ i .

• \

) \

-10 10 20

TIME. SEC

30 140 > m o n

Fig- 36 Engine Ambient and Combustion Chamber Pressure, Firing 04C

AEDC-TR-68-238

100

* 0

-100

200

CONDITIONING TARGET. -150±5tf>F-x.

X -40 -30 -10 -20

TIME", MIN

a. Main Gxidizer Valve Second-Stage Actuator, TSOVC-1

800

600

400

200

-200

B» /""

/-TFTD-8

/-IFTD-Si

TFTD-4,-^ "P*"- -«^ .CONDITIONING TARGET, 170 t'J*-^ i 1 1 L

OXIDIZE« TURBINE^ "

START TANK "C^^ / -TFTD-!

FUEL TURBINE ^2 i J (IT^ tf& -f

TCTn-»-^"'^ WT / /

( :ROSSO VERDU CT-J ITTD-3/ WD 4

-24

100 i—

-20 -IS -12

TIME. HIN


8

I -100

-200

-300

'** /

/ cc NDITIO IINGT; RGET.i D±2fl \S

-2*4 -20 -8 -16 -12

TIME. HIN



78

AEDC-TR-68-238

Q.

en Q-

5 a.

28 T moo

24- 1200

20 • 1000 rx

16+ £ 800

12+ S 600 en UJ

E 400 8-

4-

0 ■■

200

0

FUEL PUMP SP ID, NFP-1P-^

FUEL PUMP D SCHARGE PR ESSU «. P FPD-2-^

FUEL INJECTOR PRESSURE, PFJ-1A rut IAD CIS

f\ 1

PRESSUR PC-3-^ /

/ ENGINE

/ CUTOFF ¥ — J,

1 1 0 1 2

TIME. SEC


la-

s'

6-

4-

2

0-

(X ■ in

0- •

UJ oc

. tn tn UJ oc a.

1000

800

600

400

200

0

III nvini7m DIIUD

1. M DI SCHAR

rmiir

»PRESSURE, POPD- *-\| A fa y A X

- ' N \

1 ÖX1 SPE

)1ZE EM

:PUI\ OP-1

\?~\ X ^1C F :HAMI »RFSS

JER IIRF, »

Q UJ UJ

> I

V vF 'C-3

a. <n a. 1 \ ^ I / \

S^

1 ENGIh CUTOI SIGN)

JE T Jl \L-

—v_

0 1 2

TIME. SEC


Fijj. 38 Engine Transient Operation, Firing 04D

79

AEDC-TR-68-238

a. o

l_>

800

700

600

100 T ~ 500 in

80+ uj 400 E (T) 1/1 300 60

40--

tn o a.

01

UJ DC a.

200

- 20- 100

r-GAS GENERATOR FUEL

; ~ INJECTOR PRESSURE, PFJGG-2

/

/ r-G AS GENERATOR XIDIZER INJECTOR

^

/ \ ° A^ l\ ^PREbb UKE, POJGG-Z \

\ \ \ \ \ ^MAIN

\ \ 1 ,/ OXIDIZER

\ / rf y VALVE

v [ y / \ POSITION," i r\\rr

/ \ / s / / \

r \ L J u 1 j^ w ENGINE

/ \\ Cl JIOFF

GNAl 1 1 / A L-n

1

TIME. SEC

Gas Generator Injector Pressures and Main Oxidizer Valve Position, Start and Shutdown

2B00■-

2400-

2000 ■

1600+ - 500 io

cr or

1200

UJ

400-

o-

-400 ■■

800

700

600

en

400

^ BOO- 2 300

/-GAS GENERATOR OUTLET ' T LMPE RATU RE, TGG0-1A Al\ 02

K

\

\

\ \

\

—G ASG ENERAT0R C HAMBER

RESSURE, CGG-2

I Er JGINE

\ P \ C JT0FF

\ j

Y \

^-s IUNA

.—i A

1 1 «^ s

200

100

0 0 I 2 3

TIME, SEC

d. Gas Generator Chamber Pressure and Temperature, Start and Shutdown

Fig. 38 Concluded

80

■ O

00

o cr UJ n

4 6

FLOW. QF-2. GPM X I0"3


> m o O I H 70

00 to

(X

IOOOT

800-

Q_

£ 600

in ÜJ cc Q_

400 ■-

200 ■■-

0

in Q_

UJ cc ID in (O UJ CO Q_

UJ

1.0

0.8

0.6

0.4

0.2

o o

0.0

,t -CHAMBER PRESSURE, PC-3 /

/

-

TEST CELL PRESSURE. PA-2

—.

\ /

-10 -s 10 15

TIME. SEC


AEDCTR-68-238

100

Ö- 0

-100

-200

CONDITIONING TARGET, -100 ± 50°F —

• ■—

-HO -30 -10 -20

TIME, MIN


200

100

S:

-200

100

0X10IZER TURBINE -,

e^4 -.TFTD-8

CROSSOVER DUCT-' TFT">-3AN0 4

-20 -B -16 -12

TIME. MIN


-U

2 -100

1 UJ

-200

-300

\ CONDITION IMG TARGET, -1 ■» N, '

...

-at -20 -16 -12 -8 -1 0

TIME, MIN



83

AEDC-TR-68-238

28 T 1400

m i O

Q_ EC

UJ

m Q-

FUEL PUMP SPEED, NFP-1P

UMP DISCHARGE /— ruLL rumr uijunr JT" PRESSURE, PFPD-2

FUEL INJEC OR PRESSURE, PFJ-

CHAMBER PRESSURE, PC-3

0 -^-ENGINE 1 2 CUTOFF SIGNAL TIME. SEC


10-

8

6

4-

2

n.

cz ■ In

a. »

UJ cc

<n UJ cc a.

1000

800

600

400

200

0 (

m i O pi 3XID ZER »UMF SPE ■D, N 0P-1 >

X

/I OXID )ISC

ZERPUM UARfiF PRI

3

.-«IIRF Pfipn-: > a UJ UJ

/

a.

a.

r{ ;HAW »ER 'RES: ;URE, PC-:

^ ^ ■*-»-, **

^ ^-^ -*—.

•— /

) E t »GIN :UTOF SIGN/

E 1 F

TIM E. S EC

) 3



84

AEDCTR. 68-238

800

700 y-C ;AS GENERATOR FUEL

NJECTOR PRESSURE, PFJGG-2 600 / ' I

A/ 5 500 CO

r \ .

üJ 400 az

\ \ /- GAS GENERATOR OXIDIZER

in 2 300 oc

\ / NJECTOR PRESSURE, P0JGG-2

A / 0L

200 / ^ y~ ENGINE CUTOFF SIGNAL

f V } f

■— \ y- 100 s 0 _/ t-

0 ' 1 2

TIME, SEC

c. Gas Generator Injector Pressures, Start and Shutdown

2800 T

2U00--

2000

1600- « UJ DC 2 1200 + rx £ UJ £ 800 +

400-

0-

-400

800

in

oc in in UJ oc a.

l^GAS GENERATOR CHAMBER 'PRESSURE, PCGG-2

GAS GENERATOR OUTLET EMPERATURE, TGG0-1A AND 2

ENGINE CUTOFF SIGNAL

d.

TIME. SEC

Gas Generator Chamber Pressure and Temperature, Start and Shutdown

Fig. 42 Concluded

85

00

1000 T

800-

S 600 in en LU cc o_ m 400 LU CD

CE 31 t_>

200-

Q1

Lü C_)

1.0

0.8

tn o.

- - O.o LU

to LU £ 0.4

0.2

0.0

1

l

v ■

/ FEST CELL /

\ PRESSUR E. PA-2 / \ i

f £ /

r~ r.HAMRFR PRFSSIIRF PC-3 - —■»—»

^ 1 -10 -5

> m o n H t

0 5

TIME. SEC

10 15

Fig. 43 Engine Ambient and Combustion Chamber Prossure, Firing 05A

AEDC-TR-68-238

100

* 0

i •100

-200

r.nninmriKiNc TARGET. -150 ± 50°F^

-40 -30 -10 -20

TIME. HIN


a-

s s

-200

100

TIME. MIN


-100

-200

-300

\ \

\ -

CONDITIONING TARGET. -200 ± Z 5°F-,

■

-24 -20 -4 -IB -12 -8

TIME. HIN



87'

AEDC-TR-68-238

28 T 1400

2U-- 1200

20

</> 3" IH- ■ 0- a. az m

UJ • a: a UJ 12 . 3

01 UJ (/) 0- UJ en a.

a. a. 8- T- 13 a.

¥•■

01

1000

800

600

400

200

-FUE SPE

.PUR ED,N

IP FP-1 ?1

/ FUEL PUMP

/ r DISCHARGE

Dorccnor ECTOR

/ PFPC O . PDI

1INJ 'I V ■SSURE, PFJ-1A

1 1 / rKI

/ A . ^CHAMBER ' ' 1

B==

/ PRESSURE, PC-3

1

TIME. SEC


10T 1000

S: o UJ

TIME. SEC



88

AEDC-TR-68-238

0. oc

in a.

Q_

TIME. SEC


lO-i

8-

6

1000.

800

(X

■- In 600

/ -ox DIZE IPU APS 1

PEED, N0P-1P

■ O

\\ /

■x \

Q. \ —U> IUIZ LKP JMP CC

4-

• LU CC

ft 400

I DISCHARGE PRESSURE, POP D-2 •

Q LU Ld

\ Q_ V in Q_

- LU CC o- \

r-e HAMBER JE

V«, 'r KC33 JKC, ru-j

a. 2- 200

ENGINE CUTOFF I, i

SIG NAL- "^-

1 32 3 3 34 3!

TIME. SEC

d. Thrust Chamber C Ixidizer System; Shutdown

F ig. 4! 5 Co ntinu ed

89

AEDC-TR-68-238

o CC

100 T ~ 500 0.

80-f uj 400 E en

4- <"- 300

o Q.

60

40

20--

0-

UJ cc

0 1 2

TIME. SEC

e. Gos Generator Injector Pressures and Main Oxidizer Valve Position, Start

cc ID t— <x cc UJ 0- 3: UJ

2800 T

2400"

2000-

1600

1200

800

H00 ■■

0-

-400-■

en

UJ cc to UJ cc Q_

800

700

600

500

400

300

200

100

1 |

i— G ASG EMPE

ENERAT0R 0UTU H :

M RATU REr T GG0- 1A AM D2

i \ \ \ / y \ „**" i

J£—

\ /■ \

,^ V / < ^

\— RAS fi ENERAT0R _

\ -. r / CHAM BER PRESSURE. PCGG-2 > sfl _•

■ / |

0 1 2

TIME. SEC


Fig. 45 Continued

90

AEDC-TR.68-238

in a.

en in

ÖUU \

700 1

600 I \ ^GASGENERATOR 0X1DIZER

500 \ "INJECTOR PRESSURE. >0JGG-2

\ / ' 1

400 \ / 1 1 \ . ^HGAS GENERATOR :UEL

300 \ ./ iINJECTOR PRESSURE. PFJGG-2

\ y

200 j/

-A \ .CWft ur

•^ V 100 JCUTOFF

SIGNAL- L s

0 3 2 3 3 34 35

TIME. SEC


2800-1

(Z in a.

* ■ UJ

DC

<n . en

UJ <c 0.

BUU

700

600

500

400

300

200

100

0

I I I I 1 2400 .../ dGAS GENERATOR CHAMBER

jPR :SSU RE. PCGG-2

2000-

° 1600 •

WTU

RI

*-*

\ '

ÜJ

£ 800- ÜJ ^GAS .GEN ERAT( )R0U TLET

400 |TEM PERATURE, TGG0-1A AND 2

iFNG NE -

0 .CUT SIG

DFF VIAL-

\ —*| ^

-400- 1 -\ v

32 33 34

TIME. SEC


Fig. 45 Concluded

35

91

40

> rn o n

30 - m i O

X

20

CO CO

X

Q CC LÜ X

10

4 6


8 10


CO GO

luuu-

er 800 - CO - Q_ ■ ■

UJ cc 600- ZD (T) ■ ■

(/> LU CC Q_

OC 1100- UJ CO z: cc X , (-J

200-

n-

ÜJ az ZD tn LU cc Q_

<_)

1.0

0.8

0.6

0.4

0.2

0.0

PR0PELLANT UTIL ZATIC IN VALVE E> :cu RS 0N

\ \ / I 1 \

v / \ \

, i

z-l ;HAMBER PRESSURE, P

V **\

* • 1 C-3 v y *•*

/

/

, s ̂ ,

/ t

" !

4 / -l EJ>T CELL

PRESSURE, PA-2 ! t \

-10 10 20 30

TIME. SEC Fig. 47 Engine Ambient and Combustion Chamber Pressure, Firing 06A

40 > m o

OS

AEDC-TR-68-238

100

UJ

% -100

-200

CONDITION IMG TARGET, -150 ± 50°F—

--»

1 - -14D -30 -10 -20

TIME. MIM


800

600

400

300

-16 -12

TIME, MIN


100

% -100

-200

-300

_ ;

ITIONto T, 50* TARG Z5°F^

/

1

-2« -20 -16 -12

TIME. MIN

-II



94

AEDC-TR-68-238

28-1 1>400

24- 1200

m i O 20 1000

cr X •—•

(T

16- to

■ Q_ 800 .

UJ ■» oc

12 600 UJ to n UJ «o oc a. 8- 0_ 400 £ => 0_

4 - ■ 200

01

APS i-utL ru PttD, NhP-lP-,

s* s> ' -INI :CT0F

E, PFJ-1A S y r

V PRESSUR

/ / >l

/FUEL PUMP /

' DDCCCIIDC / A r- ^^

P FPD- '/. ^s

RFR -(JUMBUJ» UN ÜHAh f PRESSURE, PC-3

f •

1 2

TIME. SEC


10T 1000

m O

X

a.

0_

8-

2 ■■

01

800

er B+ en 600

4+ S 400 ui cc 0_

200

1 1 1 0XI0IZER PUMP D SCH/ WGE PRES SURE ; PO >D-1 >—.

/,

s KIDIZER PUMP PEED, N0P-1P

1 I

«BUS ESSU

-CO PR

TION CHAr RE, PC-3

ABER

1 2

TIME. SEC



95

AEDC-TR-68-238

28 T

o

X

0. cc

0- in

13

24- 1200

20+ 1000 <x

16+ a! 800

12-

8-

4-

0 ■■

moo

S 600 UJ

£ 400

200

0

\ F UEL iPEEC

SUMP - », NFP-IP > s^i

\

\

\

\* ^-FUEL PUMP DISCHARGE PR

1 I 1 I :SSURE, P FPD-2

— INJECTOR PRESSURE, PFJ-1A- - —■

1 1 1 1 ENGINE

-CUTOFF - SIGNAL-

-COMBUSTION CHAMBER DDCCCIIDC or-*

'S. 1 IlLJJU \L, 1

N 8 9

TIME. SEC


10

a. cc

UJ a. in

10T IOOO

8-

6-- to Q_

4 ■

2-

O1

cc in UJ cc

TIME. SEC


Fig. 49 Continued

96

lOO-i

80-

60-

40-

20-

0-

cr *—* <n a.

■ UJ CC => in

. in UJ

800

700

600

500

400

300

200

100

0

AEDC-TR-I »8-238

A \

z \ r-FUEL NJECTOR OXIDIZER INJECTOR PRESSURE, P0JGG-2 Q_

ED \ \ PRESSURE. PFJGG-2 1— \ LU \ CC UJ / 0-

/ z O / \i -MAIN OXIDIZER VALVE. •—4

■ POSITION, L0VT

/ r> a.

.—1 / 0 1 2

TIME. SEC


IX cc Q_ SL UJ

2800 T

2400-

2000-

1600-

1200-■

800

400

' °,'' i

-400-1

800

700

600

£ 500 IS) Q.

UJ CC

in in cc Cu

400

300

200

100

, -TEMPERATUR E, TG( 30-1A AND 2

A \ \ \ \ \ / \ ,4 *S •_

\ ,/ -CHAMBER PR ESSU RE, P CGG-2

»- ■ \ \

> \r \

. II ■

0 1 2

TIME, SEC


Fig. 49 Continued

97

AEDC-TR-68-238

in a.

cc in in UJ cc Q.

800

700

600

500

400

300

200

100

*

\ -OXIDIZ ER INJECTOR

\ Ms s' PRESSURE, POJGG-2

V s \

ENGINE CUTOFF

I ■

> k

-FUE LINJ ECTOR ^i SIG NAL- H V PRESSURE, PFJGG-2

7 ' 8 9

TIME. SEC

g. Gas Generator Injector Pressure, Shutdown

10

2800 T

2400-

2000-

1600 in a.

cc UJ £ 800-■ UJ t—

400-■

0 ■■

-400

800

700

600

500

1200 ■ uJ 400

in in CO

300

200

100

•-^s- ■—"»-< - ■•- 1

^TEMPE RATU RE, T GGO- LA AN D2

j t

*\i ^v V

run IMF . ■ j HCH AMB ■RPR ESSL RE, PCGG-2

.CUTOFF SIGNAL I

k / "V >

k / /

V V 7 e i S 10

TIME. SEC


Fig. 49 Concluded

98

m i O

CO

d LÜ

4 6

FLON, QF-2. GPM X 10"3


> m a n H x

ea ■ u u

o o

1000 T

800-■ in Q_

LU CO ID CD in LU tr

CD

cr x i_>

600- - 0.6

400-

200-

01

in a.

(_>

1.0

0.8

in in UJ

ge 0.4

0.2

0.0

CHAMBER PRESSURE, PC-3~\

\

\ V 7

/ - 1 tSrCELL

/ PRESSURE, PA-Z

I / \

-10 -5 0 5

TIME. SEC

10 15

Fig. 51 Engine Ambient and Combustion Chamber Pressure, Firing 06B

AEDC-TR-68-238 I

100

ft- 0

K I-

s UJ

£-100

-200

.

CONDITIONING TARGET, -150 ± 50°F

\>

-40 -30 -10 -ao TIME. HIN


S

-16 -12 -8

TIME. HIN


5 -100

-200

-300

\_

\ \

ICONDIT .TARGET

I0NING -250±25°r-^

\

) ■

-21 -20 -16 -12 -8 -1 0

TIME. HIN



101

AEDC-TR-68-238

X

JE a. oc

0_

a. z:

28

24

20-1- 1000 cc

16+ £ 800

12-

8-

4 ■■

0-

moo

1200

§ 600 Ul a. 400

200

0

FUE L PUMP SPEED, NFP-lP->

\ run PI IMP

1 />

-

OISCHARGE PRESSURE. PFPD-2^ / 1 1 1

,1»,

/' INJECTOR rnu jurvc, rrj- iAfc=^

\

A' ^-C( )MBUSTIO

tESSURE, M CHAMBH \

PI PC-3

1 1 1 2

TIME. SEC

d. Thrust Chamber Fuel System, Start

o

X

Q_ 0C

0_ en a.

o.

TIME. SEC



.102

AEDC-TR-68-238

o

X

a. oc

0. in

3 a.

28 T

24 ■■

20

16

12

8

o-l

moo

1200

1000

a. 800 UJ

UJ oc

33 34

TIME. SEC

e. Thrust Chamber Fuel System, Shutdown

a. oc

UJ UJ Q_ (O

a.

CL-

IO T looo r

8- 800

cc_ 6+ In 600

4- ■ % 400 UJ oc Q.

2 ■■ 200

0-L

A / RPl -^OXIDIZ IMP SPEED, N0P-1P 1 1 l

\\ r' 1 1 1

\ t F IXIDIZER PUMP PRESSURE, POP

DISCHARt 5-2

it

V \ A ^V

-COMBUSTION CHAA PRESSURE. PC-3

ABER

v

32 33 34

TIME. SEC


Fig. 53 Continued

35

103

AEDC-TR-68-238

800

700

600

IOO-I sno 2* in UJ 0_ Q_ O 80- ' UJ 400 1— cc z ^ UJ tn rr 60 . io

UJ 300 LU oc Q_ o_

z 40- 200 o *-^

to 20- 100 « 0_

0- 0

bxiDIZERINJEI ;TOR GG-2 K PRESSURE, P0J

ft / \ rzFUEL INJECTOR . ^^ \ T PRESSURE, PFJGG-2 ,

\

A <*>' r ̂ -MAIN0XIDIZER

/ N\ \ VALVE POSIT ON, LOVT f

\ A ^

. 1 /

TIME. SEC

e. Gas Generator Injector Pressures and Main Oxidizer Valve Position, Mart

oc ID I— <X OC UJ a. •XL UJ

2800-1 800

700

600

5 500 a. UJ* 400 oc is tn

■ SS 300 oc a.

200

100

0

rT JVIPEF IATUR JL TGGO-IA AN 32 2400-

/

2000- A '\

1600- i / \ \ / V \ / \ ldUU' \ / \ -

800- \ / j t~

\ / /

400- \ f A i-

V / —C HAME ERP RESS URE, PCGG-2

0- \ (* -H •*-*. \ -7 r»—■%*■

-400- 71 0 1 2

TIME. SEC


Fig. 53 Continued

104

800

700

600

500

400

300

200

100

0 3

800

700

600

500

400

300

200

100

0

■

AEDC-TR-68-238

\ ■ I V- —IGKID17ER INJEC1 rriR

■

\ PRESSURE. P0JGG-2 er \

i o_ \

LiJ

tr> in s

LU

- -

•ENGINE - .CUTOFF SIGNAL-

I Xi N i -FUE LINJ ECTOR

H PRESSURE, PFJGG-2

2 ' 33 . 34 35

TIME. SEC


£OUU-

cr <n Q_

• - LLl

OC

tn . v>

UJ oc ü_

2400- -

2000-

*" 1600- • UJ

r-TE MPERATURE, TGG0-1A ANE )2 ■

/ oc £ 1200- s

k V \j

*■

UJ

£ 800- UJ

V -

• ;HAM BER »RESSURE, PCGG-2 400- i

JCKir MC i

0- CUTOFF SIGNAL-

I V i S

-1400- J V 32 33 34

TIME, SEC


Fig. 53 Concluded

35

105

ro i O

o

cr

> m o n ■

70 i.

4 6

FLOW. QF-2. GPM X 1CT3


o

1000T I.O

800-

O1

0.8 m cr Q_ »—4

in • Q-

UJ cc ROO- • 0.6 =D UJ in cc en Z) LU in DC in Q_ UJ

DC 400- . cc r a. 0.4 ÜJ CD —1 > —I <X UJ X (_> u

200-- 0.2

0.0

\ -PROPEUANT UTILIZATION

\ VALVE EXC JRSION

\ > /

_y ^ •-~

f ^

— ÜHAMBtK

PRESSURE, PC- 3

■TEST CELL PRESSURE, PA-2 —-» /

t f _.

.*■*

y / \

.-10 10 20 30

TIME. SEC

Fig. 55 Engine Ambient and Combustion Chamber Pressure, Firing 06C

40 >. m o O H

« CD ■ to w

AEDC-TR-68-238

100

r—

S £ -100

-200

CONDITIONING TARGET, -ISO* Hft-

\ y

V

-40 -30 -10 -20

TIME. HIN

a. Main Oxidizer Valve Second-Stage Actuator, TSOVC-1 0XLDIZER TURBINE-i

START TANK -TFTD-B

800

600

400

200

-200

FUEL TURBINE Js<(

CROSSOVER DUCT J tTFTD-JAND4

r-TFTD -1 /-TFTD-?

rTFTD-4

TFTOV y CONDITIONING TARGET. 170*.

(AS INDICATED BY TFTD-3ANC >-

/ 41

1 1

-24 -20 -16 -12 —8

TIME. HIN


? -100

I ÜJ r—

-200

-300

N v \

i :ONDIT ONING [ARGET -200 ± 25°F-

v

V 'V\; __

'

-24 -20 -8 -16 -12

TIME. HIN



108

AEDC-TR-68-238

Q. tC

a. in

a:

28 T 1400

24 ■■ 1200

20 ■■ 1000 -

16+ £ 800

12-

8

4-

0--

S 600 <n LU

£ 400

200

0

FUEL PUMP SPEED, NFP-1P- -

-FUE PRl

LINJECTOR LSSURE, PFJ-1A

/ F UEL PUMP IISCHARGt »DPCCIIDF i

f L f ' ,tt

/ W"S

/,** ^C HAMBER PRESSURE PC-1

/ / #

t==

/

1 2

TIME. SEC


a. a:

CL to

a. s: a.

10T

8-

6-- m o_

M J. CO ■•T in LU

Q-

2 ■■

O-1-

1000

800

600

400

200

UXIUIZtK PRESSUR

HUM E, PO

PDISCHARGE PD-2-i

\ -OXIDIZE \ PUMP S 3EED, NOP -IP /

\ \ s y*

J s ^^ -CHAMBE *PR ssu IE, P :-3

h j / 1 J

J 1— '■ v f

J 1 2

TIME. SEC


Fig. 57 Engine Transient Operation, Firing 06D

109

AEDC-TR-68-238

28 T 1400

24- 1200

2 20 x

16 o.

UJ Q-

0.

Q_

3 Q_

12

8-

4..

01

1000

Q. 800

cc

in CC

600

400

200

TIME. SEC c. Thrust Chamber Fuel System, Shutdown

10 T 1000

8-

6-

4-

2 -

01

TIME. SEC


Fig* 57 Continued

110

AEDC-TR-68-238

Q_ o

Ui

ec

o a.

IOOT 5 a.

80- UJ* CO => tn

60- «S az a.

40-

20 ■

0-

800

700

600

500

400

300

200

100

/■ -GAS GENERATOR FUEL INJECTOR

/ PR :SSURE, POJGG-2

/ y

\ WO UtntKAl

-OXIDIZER INJECTOR PRESSURE.

OR s /

\ / \ / \ P0JGG-2n y

v / \ -i f \ /

^ \J, rMAIN OXIDIZER VALVE 1 POSITION, LOVT /

1 /

TIME. SEC


2800 T

2400 ■■

2000-

ÜJ

cr cc UJ

s: ÜJ

800

400-

■ . o-■

-400■■

BOO

700

600

1600+ - 500 to 0.

1200+ UJ 400 ac

J- £ 300 oc a_

200

100

0

-GAS GENERATOR OUTLET TEMPERATURE, TGG0-1A AND 2

A \ —•~—~*

\ / \ \ / \ >

1 v / r ̂ G ASG ENERATOR CHAMBER

\ / / PRESSURE, PCGG-2

\ / /

\ v rJ V r' -

•1 1

TIME. SEC


Fig. 57 Continued

111

AEDCTR-68-238

a.

in

Q.

tiUU

700

600

500 \ \

V IS GENERATOR OXID ZER 400

of

\\ INJECTOR PRESSURE, P0J6G-2

300 V —GJ tS GENERATOR FUEL INJECTOR (ESSURE, PFJGG-2

200 > ** PF

r ^ ■—

100 FNG NF I CUTOFF N s.

n SIGI <AL- v 7 8 9

TIME. SEC

g. Gas Generator Injector Pressures,-Shutdown

10

2800

2400

2000

800

400-

0 ■■

-400-

800

700

600

1600+ ~ 500 to a. 12004- uj 400

UJ to 'J- 2 300

rr

200

100

0

— G *SG :NERATOR CHAW BER P RESSURE, PCGG-2

/ -GAS GENERATI DROL TLET

\i / TEW PERATURE, TGG0-1AAND 2

V

FMR NF I CUTOFF ^ SIGI MAL— \

8 10

TIME. SEC

h. Gos Generator Chamber Pressure and Temperature, Shutdown

Fig. 57 Concluded

112

• i O

00

I

X

CD cr

4 6

■ FLOW, QF-2. GPM X 10"3


> m o n

u 00

1000 T

800-■ <r> cc Q_ •—4

CO • Q_

LU cc 600- ■h

Z> LU (O CC to ID LU to CO CO Q- LU

CC LIOO- . QC Q_

LU CO _l s: _l er LU z: (_) C_)

200--

ÜL

1.0

0.8

0.6

0.L1

0.2

n

0.0

CHAMBER PRESSURE. PC-3-< \

~\ c '

/ / -

/

/ Itbl UtLL i /

<*■ ■

PRESSURE, PA-Z^ t~ -f

j

r \ 1 -10 -5 0 5

TIME. SEC

10 15


AEDC-TR-68-238

100

i— er EC

-100

-200

CONDITIONING TARGET, -UOlSlfr^

- s»

,.

-40 -30 -10 -20

TIME. MIN


200

100

B o

-100

-200

0X1

START TANK A

HZERT URBINE

V, TFID-8

TFTD-2^^ «7

CROSSOVER DUCT-' ^FTD-SAND* 1 1 l l 1

r-T 7D-8

1 1 1 1 1 CONDITIONING TARGET, -100±ZOPF-v

pTFTD-4 X "^ 7D-2 ^TFTD-3

-21 -20 -IB -12 -B

TIME. MIN


100

2 -loo E

-200

-300

cot ID IT ION INGTA IGET, - tx>±& *"\ V

\

JN

-2>1 -20 -8 -IS -12

TIME. MIN


Fig. 60 Thermal Conditioning History of Engine Components, Firing 06E

115

AEDC -TR-68-238

24-

20-

16

12

8-

4-

0-

IHUU

1200

1000 a

o- 800.

UJ

S 600 to UJ

■ E 400

200

• n

m FUEL PUMP SP EED. MFP-] l'-\ O 1 1 \ X

FUEL INJECTO R FJ-1A

-FU EL PUMP Q_ EC PRESSU RE, P \ DISCHARGE PRESSURE,

• rtru-c

UJ UJ / \ in f

\ / QL

ID ENG

1 : SIG WL4 \ J

Q_ Ntl /

UlOh \\ /\ j V ^-CHAMBER PRESSURE, PC-3

/ - *u M *x r A

s== /

mi-!» -^- y C a*£^> -jyil

*»^-|--s.M_i

0 1 2

TIME. SEC


10T IOOO

m I o

Q_ CC

Q_ (O

Q.

8-

6 ■

2-

01

800

<n 600 OL

gc

4+ £ 400 UJ cc a.

200

rc iXIDI ZER >UMP SPEED. N0P-1P

1 *

/-< 1 1 1

)XIDIZER PUMP DISC :HAR( IE

/ f >RESJ 1URE, POPD-2 1 1 1 1 1 /

^EN SINE CUTOFF SIGNAL | |

/ ^-CHAMBER

•c ■^/v

•/

r P

K£33UKr.,

C-3

/

fs V ^f "V /"■

-/ < -—<* •^~ J r i 0 1 " 2

TIME. SEC


Fig. 61 Engine Transient Operation, Firing 06E

116

AEDC-TR-68-238

o cc

800

700

600

100 T ? 500 to O-

80+ uj 400 oc

£ 300 oc OL

BO

40

01 o 0-

01

200

« 20- 100

>^GAS GENERATOR FUEL INJEC rOR PRESSURE, PFJGG-Z

Ir-GAS GENERATOR OXIDIZER

/ NJECTOR PRESSURE, POJGG-2 '

,r- MAIN OXIDIZER VALVE POSITICH X ̂ /

' X > A XJ ■v -

LOVT

1 --'^ -T 1 -^ 1 \ -ENGINE CUTOFF SIGNAL "A \

. \ \ 1 1 1

TIME. SEC

Gas Generator Injector Pressures and Main Oxidizer Valve Position, Start and Shutdown

oc

EC

2800 T

2400 ■

2000-

1600

1200

800

400-

0-

-400-

a.

oc m to LU OC Q_

800

700

600

500

400

300

200

100

TIME, SEC

Gas Generator Chamber Pressure and Temperature, Start and'Shutdown

Fig. 61 Concluded

^-G AS GENERATOR UTLET TEMPERATURE, 0

l( iliU- A AN DZ

IS

\ V v V •\ -

\ \s \

\ \

l ^-G AS GENERATOR HAMBER PRESSURE, CGG-2

i i i

v s\ s* C

\ . 1 / \ \

■ > H — -

\" .— ENGINE CUTOFF SIGNAL

1 V 0 i » 3

117

X

Q (X Lü X

n -i

4 6

FLOW, QF-2. GPM X !0"3

Fig. 62 Fuel Pump Start Transient Performance, Firing 06E

CO

en Q_

0C Z>

in LU CC 0_

CC LU GO

cc

1000 T

800 --

600 --

400-

200-

0

to

LU DC => in in LU

LU

1.0

0.8

0.6

0.4

0.2

0.0

"

TEST CELL PRESSURE, PA-2 ^v \

\ V *

S f \ V J

--! CHAMBER PRESSURE, PC-3

JU S *

fc h t \

-10 -5 0 5

TIME. SEC Fig. 63 Engine Ambient and Combustion Chamber Pressure, Firing 06E

10 15 > m O n ■ -\ 7) ■

09 ■

W

AEDC-TR-68-238

TABLE I MAJOR ENGINE COMPONENTS

Part Name P/N S/N

Augmentec Spark Igniter (Te3ts 03 and 04)

Augmented Spark Igniter (Tests 05 and 06)

Augmented Spark Igniter Oxidizer Valve

Auxiliary Flight Instrumentation Package

Electrical Control Package

Fuel Bleed Valve

Fuel Flowmeter

Fuel Injector Temperature Transducer

Fuel Turbopump Assembly

Gas Generator Control Valve

Gas Generator Fuel Injector and Combustor

Gas Generator Oxidizer Injector and Poppet Assembly

Helium Control Valve (Three-Way)

Helium Regulator Assembly

Helium Tank Vent Valve

Ignition Phase Control Valve (Four-Way)

Mam Fuel Valve

Main Oxidizer Valve

Main-Stage Control Valve (Four-Way)

Oxidizer Bleed Valve

Oxidizer Flowmeter


Oxidizer Turbopump Assembly

Pressure-Actuated Purge Control Valve

Pressure-Actuated Shutdown Valve Assembly

Primary Flight Instrumentation Package

Propeiiant Utilization Valve

Restartable Ignition Detect Probe

Start Tank

Start Tank Discharge Valve

Start Tank Fill/Relief Valve

Start Tank Vent and Relief Valve

Thrust Chamber Body

Thrust Chamber Injector Assembly

206280-161

309360-91

308880

704090-21

502670-51

309034

251225 -

NA5-27441

460390-181

309040-31

308360-11

303323

WA5-27273

558130-11

NA5-27273

558069

409920

411031-21

558069

309029

251216

409940

458175-111

558126

558127-11

704095-21

251351-51

500750

307579

304386

557998

557848

15-205875

208021-11

4084016

4071414

4079065

4075163

4081742

4084042

4074110

AA13283F66

4073647

4055754

4090408

4092975

372452

4061139

379313

8313398

4074288

4072666

8284312

4078081

4075154

4073096

6610105

4073862

4074549

4074730

4075182

2125567

0098

4086957

4091617

4080517

4062445

4089721

120

TABLE II SUMMARY OF ENGINE ORIFICES

to.

Orifice Name Part

Number

Diameter, Inches Unless

Otherwise Noted

Date Effective

Comments

Gas Generator Fuel Supply i-ine

RD251-4107 0.488 July 15, 1968 -

Gas Generator Oxidizer Supply Line .

RD251-4106 . 0.284 July 15, 1968

Oxidizer Turbine Bypass- Valve Nozzle

RD273-80Ö2 1.520 July 15, 1968

Main Oxidizer Closing Control Line

710437-083 411039X4

8.30 scfm 8. 75 scfm

July 5, 1968 August 5, 1968

Thermostatic Orifice

Oxidizer Turbine Exhaust Manifold

RD251-9004 10.00 (1)

-.

Augmented Spark Igniter Oxidizer Supply Line ■

309358 0. 125 June 9, 1968

Augmented Spark Igniter/Fuel Supply Line

0. 266 0. 302

July 26, 1968 August 5, 1968

No Orifice Used for Test 03

(1)As delivered to AEDC

> m O n

70

to

AEDC-TR-68-238

TABLE III ENGINE MODIFICATIONS

(BETWEEN TESTS J4-1901-03 AND J4-1901-06)

Modification Number

Completion Date

Description of Modification

Test J4-1901-04

RFD-AEDC 37-1-68

August 5, 1968 Rerouting of Start Tank Discharge Valve Drain Line

RFD-AEDC 19-68

l

August 5, 1968 Retiming Main Oxidizer Valve to

1650 „ msec — Cl\J

RFD-AEDC 42-68

August 5, 1968 Retiming Gas Generator Oxidizer Valve Opening Delay to

loO _Q msec

Test J4-1901-05

LRFD - Rocketdyne Field Directive

TABLE IV

ENGINE COMPONENT REPLACEMENTS (BETWEEN TESTS J4-1901-03 AND J4-1901-06)

Replacement Completion Date

Component Replaced

Test J4-1901-04

UCR1

R005151 August 5, 1968 Augmented Spark Igniter Assembly -

Test J4-1901-05

UCR - Unsatisfactory Condition Report

122

TABLE V ENGINE PURGE AND COMPONENT CONDITIONING SEQUENCE

Time, min

1-40 I - 30

to to

Turbopump and Gas Generator Purge (Purge Manifold System)

Helium; 82 - 130 psia 50 - 200* F

(Nominal 6 »rfm at Customer Connect

2-mm Minimum—-j

Wi/i/i 1 f 1 to 3 min -m\ ■»■ Propellant Drop

Oxidizer Dome and Ga» Generator Liquid Oxygen Injector (Engine Pneumatic System)

Helium; MOOpsig 50 - 100* F

(Nominal 230 scfm at Customer Connect)

1 sec (Supplied by Engine Helium Tank during Start and Cutoff Transients, —fa- Purge on for Duration of Fuel Lead at Engine Start)

m Wi/i/i Oxidizer Dome (FacUity Line to Port C03A)

Nitrogen, 415 - 675 psia 100 - 200" F 175 - 230 scfm

On at Engine -* Cutoff wm ■ ■ W/i/i/k Wi/i/i W/i/i WM/i ■

Oxidizer Turbopump Intermediate Seal Cavity (Engine Pneumatic System)

Helium. 1400 psig 50 - 20O"F 2600 - 7000 acfm M Wi/i/i (Supplied by Engine -4*

Thrust Chamber Jacket (Customer Connect Panel)

Nitrogen, 165 215 psia 100 - 200*F

Nominal 100 acfm

On at Engine -• Cutoff W/////M ill Wi/i/i Wi/i/i W/i/i

Helium; 55 - 200 psia Ambient Temperature 1

Thrust Chamber Temperature Conditioning

Helium, 1000-psia Maximum Temperature as Required

1

Wi W/i/M Pump Inlet Pressure and Temperature Conditioning

Oxidizer. 35 to 48 psia -298 to 280* F

Fuel, 28 to 46 psia -424 to 416*F

Wi/i/i Wi/i/i W/////M Wi/i/i Wi/i/i Wi/i/i Hydrogen Start Tank and Helium Tank Pressure and Tem- perature Conditioning

Hydrogen; 1200 - 1400 psia -140 to -300-F

Helium; 1700.- 3250 psia -140 to 300"F

Wi/i/i W/i/M Crossover Duct Temperature

Helium; -300»F to Ambient

i

Wi/i/i Wi/i/i Wi/i/i W/i/i Wi/i/i W/ii/ik Wi/i/i Start Tank Discharge Valve

Helium, Ambient Wi/i/i W/i/M Conditioning Temperature to be Maintained for the Last 30 min of Pre-Fire

o o U TO

OS

TABLE VI

SUMMARY OF TEST REQUIREMENTS AND RESULTS

to

■ - —

C D

Target A.,,,,, Target Actual Target MM 1 Target MM Time uf Day, br/Firing Date 114.1 -

7/23/68 1408 i 7/2.1/68 163T ' 77 33/88 1704 " 7/23/68 PraMura AIDILK!.' ai Engine Start, rt (Ref. U ion.oon 100, 000 100,000 106,000 loo, onn 106, onn i no. (KM 104, 000

Firing Duration, sec*5 32. 5 11. 575 7.5 7.588 32.5 32.576 7. 5 1, 2fi4

Fuel Pump Inlet Conditions at Engine Start

Pressure, psia «••!} 41.6 "•»!2 27. 1 ».,:» 27. 1 26.5 +; 27.0

Temperature, *F -421.4 ±0.4 -421.0 -421. 4 ± 0. 4 -421.3 -421.4 ±0.4 •421.7 -421.4 ±0.4 -421.2

Oxidixer Pump Inlet Conditions at Engine Start

Pressure, psia 32.0*1 33.6 45.0 *J 45. 1 45.0 *J 45.6 1 4S.0*J 45.0

Temperature. 'F -295. 0 1 0. 4 -295,0 -295.0 ± 0. 4 -295.3 -295.0 ±0.4 -295.1 -295.0 ±0.4 -285.1

Start Tank Conditions at Engine Start

Pressure, psia 1400 t 10 1369 1300 i 10 1301 1400 1 10 1389 1300 ± 10 1297

Temperature, *F -200 * 10 200 -215 ± 10 -214 -200 ± 10 -20.1 -265 ± 10 -2GB

Helium Tank Conditions at Engine Start

Pressure, psia 2066 2240 2065 2023

Temperature, *F -193 -213 -iss -265

Thrust Chamber Temperature Conditions at Engine Start/tn, *F

Throat -«•'To -64 +50 ± 50 + 72 -250 ± 25 -242 +50 ± 50 +82

AverageEngine Start/In J^~~~~^2M

+43 __ " _^^--"^-277

-256 ----*~ y +45 __^---J'

Crossover Duct Temperature

at Engine Start, *F®

TFTD-2 +34 + 455 + 33 + 436

TFTD- . -4 »1 +49 «1? + 186 ^^** 50 2 -50 450 '»:." tiei ^/0t00*

-*"* 19 ;J

TFTD-8 440 +438 + 3S + 434

Main Oxldizer Valve Second-Stage Actuator

Temperatur* at Engine Start, 'F® -150 ± 50 -146 -150 ± 50 -146 -150 ± 5U -158 -150 ± 50 -154

Fuel Lead Time, see® 3. 0 :i oi8 8. 0 7, »21 3.0 3.021 8. 0 7.937

Propellant in Engine Time, min 30 129 25 30 149 27

Proppllant Rei-irculaTion Time, min 10 12. 1 10 10 ID 15 10 18

Start Sequence Logic Normal Normal Normal Normal Norms! Normal Normal

Gas Generator Oxidize r Supply Line Temperature at Engine Start, "F

TOBS-2A + 54 + 1F + 37 ,4

TOBS-3 + 29 + 18 +26 + 19

TOBS-4 + 54 448 °:) I 451

Start Tank Discharge Valve Body Temperature at Engine Start, *F

+ 31 4 -28 -41

Vibration Safety Counts Duration, msec, and Occurrence Time, sec, from t0 ^^**0. 978

6 ^^"

^0^*"- 960

35 -S**'

M^**0- 9«4

5 ^^^"

Gas Generator Outlet Temperature, "F

Initial Peak 1560 1760 1840 2190

Second Peak 1930

Thrust Chamber Ignition (Pr - 100 psia) Time,

sec (Ref. t0)® 0.979 0.961 1.073 0. 93S

Main Oxidiaer Valve Second-Stage Initial

Movement, sec (Ref. to)© 1.005 1. 183 1.095 1. lBli

Main-Stage Pressure No. 2, sec (Ref. InrG 1.579 1. 645 1.604 D

Time Chamber Pressure Attains 550 psia, sec

(Ref. to>® 1. 848 1.993 1.951

Propellant Utilization Valve Position,

Engine Start/tn + 10 sec

Null ^r**' Null^^**-"" Open Open

Null ^***~

-<^^**^losed

Null -s**' Open «.

> m o n ■ -i TO

is

U CO

Notes; '"'Data reduced from oscillogram. "'Component conditioning to be maintained within limits

for last IS min before engine start. ^Component conditioning to be maintained within limits

for last 30 ruin before engine start or coast duration, whichever is longer.

TABLE VI (Continued)

to

04A 04B 04C 04 D 05A

Target Actual Target | Actual Target | Actual Target | Actual Target | Actual Time of Day, hr7 Firing Date uu—. ' ' fllUt» *"" frnir.% l527. . '—7/11 /»ifl 1533 : tit ras Pressure Altitude at Engine Start, ft (Ret. 1) tU'J, '.u.U..' 7H, 000 100.000 100, 000 100, 000 100.000 UK), DOil i to. nno 100,000 104.000 Firing Duration, sec$ ;.: :', 25.U20 7. 5 7.580 32. 5 32.573 7. 5 1.994 32. 5 0. 448

Fuel Pump Inlet Condition* at Engine Start

Pressure, psia 26-5!o 27. 9 1 26.5 *£ 27.0 41.0 ± 1 40.6 1 41.0 ± 1 40.8 II 41, 0 ± 1 41. 3

Temperature, *F -421.4 ±0.4 -421.5 ■ ■ . ■ 0.4 -421. 1 -421.4 ± 0.4 -421.5 1 -421.4 1 0.4 -421. 3 1 -420.4 ±0.4 -420.6

Oxidizer Pump Inlet Conditions at Engine Start

Pressure, psia *••!{ 45.2 | 45.0 to 45.4 45. 0^ 45.8 1 45.0 *p 45.8 1 33.0 ± 1 32.7

Temperature, *F -295.0 ±0.4 -205.1 -205.0 ± 0.4 -295.2 -295.0 ± 0. 4 -295. 1 1 -295.0 ±0.4 -294, 8 1 -294.5 ± 0.4 -294.8


Pressure, psia 1400 i 10 1381 1300 t 10 1291 1400 1 10 1400 1 1300 ± 10 1204 1400 i 10 1374

Temperature, *F -300 t 10 -21S -265 i 10 -26S -200 * in -207 1 -265 ± 10 -262 -140 ± 10 -142

Helium Tank Condition» at Engine Start

Pressure, psia 2041 2160 2158 2207 2122

Temperature, *F -204 -263 f -204 -259 -140

Thrust Chamber Temperature Conditions at Engine Start/t0, *F

Throat *!5 -67 +50 ± 25 +71 -»!3 -71 1 +50 t 25 +76 -™5 -154

Avorage Engine Start/to

-71 _--—-"" ^-^ -178 ..- -~""*^294

-78 _-^*"|| «~~~~~^ -22«! rf-""""*"^ -3491

-142 --—-" tf**-*^ -176


at Engine Start, "F®

TFTD-2 + 35 +424 ♦ 18 +433 -101

TFTD-3/-4 "•3. -.45 - " ^->-~*^ +48 ,m«« + 185^,^-—^ + 5n*°

^—--^ + 192| -50 ♦34^~—'[ +170 +l° * !53-^*"""+1671 ■J 00 * 20 -86 _^~-"^

^00»^^ -85

TFTD-8 + 44 +412 + 22 +410 -87

Main Oxidixer Valve Second-Stage Actuator

Temperature at Engine Start, *F® -150 i r>o -106 -150 ± 50 -132 -150 i 50 -151 -150± 50 -146 -100 i 50 -142

Fuel Lead Time, »ec© ■ i 3.01S 8.0 7. 934 i i) 3 021 8.0 7.938 1. 0 0.998

Pro pel laut in Engine Time, min 30 3U 3.0

Propeliant Hecirculation Time, min 10 10 10 17.5 10 24.5 10 10 10 10

Start Sequence Logic Normal Normal Normal Normal Normal Normal | Normal Normal Normal Normal

Gas Generator Oxidizer Supply Line Temperature at Engine Start, 'F

TOBS-2A +60 + 29 «1 + 10 + 24

TOBS-3 +44 + 31 ,37 | + 27 + 36

TOBS-4 +58 + 49 +53 + 37 +58

Start Tank Discharge Valve Body Temperature at Engine Start, *F

+55 + 3 -51 -53 50 1 2S « Vibration Safety Counts Duration, msec, and Occurrence Time, sec. froni In _^****0. 978

15 -^"*"

^0^\, 04fi J^****0. 956 | ^^^"0. 948 XT Gas Generator Outlet Temperature. #F

Initial Peak 1870 1940 1960 2010 ... Second Peak 1750 2120 | 2160

Thrust Chamber Ignition (Pc = 100 psia) Time,

sec (Ref. t0)<D 0.962 0.945 0.858 0.948

Main Oxidiier Valve Second Stage Initial

Movement, sec (Ref. to)® 1. 085 1. 196 1. HI 1. 222

Main-Stage Pressure No. 2. sec (Ref. t0t® I, 5B2 I, Ml 1.579 1 1. B42 ... Time Chamber Pressure Attains 550 psia, sec

(Ref. t0)d> 1.821 2.01)5 1.607 1.964

Propeliant Utilization Valve Position, Engine Start/to 4 10 sec

Null^^^^ _^^""Cloaed

Null ^*-**'

_^-****Cloeed Open Open Null ^^^~

^^-^^Closed

Null ^^***"

^^-^'Closed Open

1 Null ^^"" <*«■ IJ>£os,d Null

Notes: Data reduced from oscillogram. ^Component conditioning to be maintained within limits

for last 15 min before engine start. ^Component conditioning to be maintained within limits

for last 30 min before engine start or coast duration. whichever is longer.

o

t CO 00

TABLE VI (Concluded)

to Oi

■ A B C D

Target Actual Target A,,,.,, Target Actual Target - Target Actual

Time of Day. hr/Firin« Dale 6718/68 1514 B/15/6B.

1846 _^ ■—iris/ee 1917 1716761 -— ■ Til/ft« Pressure Altitude at Engine Start, ft (Ref. ll 100,00U B;>, ooo 100.000 89,000 100.ÜU0 11)3. 000 100.000 103. 000 100.000 110, 000 Firing Duration, secCP -■.' ■ 12.574 r.i 7. böU 32.5 32.574 7. 5 7. 585 1. 25 1. 251

H Fuel Pump Inlet Conditions Prasaure, psia »•tj 2-;. 2

26-5-i J H, n 26"5-0 26.2 H.I t{ 26.4 26.5 « 27. 2

II at Engine Start Teropersture, "F -421.4 ±0.4 -421.3 -421.4 z 0.4 -420. 6 -421.4 ±0.4 -421.7 -421.4 ±0.4 -421.2 -421.4 ±0.4 421.2

1 Oxidizer Pump Inlet P™."". m* 33. 0 i 1 33. 7 45.o :0 45.4 MUOtJ 33.7 45.0 tÖ 45.2 33. 0 +J 32.0

1 Conditions at Engine Start Temperature, *F -295.0 i 0.4 ■295.4 -295.0 1 0.4 -295.2 -295. 0 ± 0.4 -294.9 -295. 0 t 0.4 -284.7 -295.0 ±0.4 -293.9


Pressure, psia 1250 | 10 125Ö 1300 ± 10 1313 1250 + 10 1263 1300 ft 10 i:il2 1250 ± 10 1254

Temperature, *F -140 * 10 -143 -265 ± 10 -267 -140 ± 10 -140 -265 t 10 -265 -140 ± 10 137

Helium Tank Conditions at Engine Start

Pressure, psia 2081 2081 2066 2081 2445

Temperature, *F -129 -257 -136 -261 | "" Thrust Chamber Temperature Conditions at Engine Start/to, 'F

Throat -200 ft 25 -203 *50 ft 25 +72 250 ft 25 -248 -200 ft 25 -217 - 200 ft 25 -199

Avvraga Eogfna Start/to

-185 __---*' ___-—" -367

+24 __—-*" ...— ""^ -279

-241 _---' _^-— -342

-206 __--~~ ^-~ -370

-201 -—-"*


at Engirt« Start, *F®

TFTD-2 -10» +406 -110 +409 -no TFTD-3/-4 • 100 i 20

-76 _----'"' __^-—"^ -77 ±170*0

+ 174 _-—-^ ^~"^ * 185 -100* 20

-86 __-—'■■" ^—-""^ -85 *.™:;5

,^--"*+186 - 100 ± 20 -95 __—~-~~

TFTD-8 -90 +406 -93 + 415 -100

Main Oxidize r Valve Second-Stage Actuator

Temperature at Engine Start, *F® -ISO 1 50 -121 -150± 50 -147 -150 ft 50 -176 -150 ft 50 171 -ISO ± 50 -184

Fuel Lead Time, sec® H. 0 7. 938 8.0 T.I8S 3.0 3. 022 8.0 7. U36 8. 0 7.938

Propellant in Engine Time, min 30 30 30

Propellant Reclrrulation Time, min 10 10 10 14 10 10 10 11.5 10 10

Start Sequence Logic Normal Normal Normal Normal Normal Normal Normal Normal Normal Normal

Gas Generator Oxidizer Supply Line Temperature at Engine Start, "F

TOBS-2A *n + 3 -8 -10 - TOBS-3 +30 + 19 + 19 -5 , TOBS-4 + 4S +50 +41 ♦ 34 .42

Start Tank Discharge Valve Body Temperature at Engine Start, *F + 76 +24 + 12 -16 + 26

Vibration Safety Counts Duration, msec, and Occurrence Time, sec, from' tn _^-^l. 054

21 -^^

_^^**0. 950

3 3 ji**'

^^^%, 052

25 -0^

,^*"**(>. 960

G*a Generator Outlet Temperature, *F

Initial Peak 1450 1730 2020 1930 1840

Second Peas 1760

Thrust Chamber Ignition (P, ■ 100 psia) Tune,

see (Ref. t0)® 1.091 0.953 1.062 0.972 1.093

Main Oxidizer Valve Second-Stage Initial

Movement, Bee (Ref. to'® 0. 987 1. 115 1.004 1.096 1.014

H*dn-VtM*Pr«Mtn Ha 2. Me (Bat tsjB 2. in 1. 7hfl 1.804 1.689

Time Chamber Pressure Attains 550 psia, s&c

(Ref. t0)® 3.233 2.013 2. 124 2.090

Propellant Utilization Valve Position,

Engine Start/to * 10 sec Open^"

_^-"*Clused

0\w\s*^ Open Open

Null^-*""' Null^"""

^-^''Cloced Op.„ Open Null Null

Data reduced from oacillogram. »Component conditioning to be maintained within limits

for last 15 min before engine start. ^Component conditioning to be maintained within limits

for last 30 min before engine start or coast duration, whichever is longer.

> m o n • H TO

Ö. CO I to

TABLE VII ENGINE VALVE TIMINGS

to

Firing Number J4-1901-

Start

Start Tank Discharge Valve Main Fuel Valve Main Ihulir.ci

First Stag Valve

• Main Oxidizer Valve

Second Stage Gas Generator

Fuel Poppet

Gas Generator Oxidizer Poppet


Time of

Opening Signal

Valve Delay Time, sec

Valve Opening Time,

sec

Time of

Closing Signal

Valve Delay Time,

sec

Valve Closing Time,

sec

Time of

Opening Signal

Delay Time, sec

Valve Opening Time,

sec

Time or

Opening Signal

Valve Delay Time,

sec

Valve Opening Time.

sec

of Opening Signal


Valve Opening

Time, sec

Time of

Opening Signal


Valve Opening Time, sec

Time of

Opening Signal


Valve Time Opening' of Time, Closing sec Signal


Valve Closing Time,

sec

03A 0.0 0. 129 0. Ml 0.450 0. 128 0.248 -3.018 0.076 0. 102 0.450 0.056 0.052 0. 450 0.645 1.882 0. 450 0. 108 0.030 0.450 0. 185 0.077 0.450 0.211 0.286

03B 0.0 0. 131 0. 113 0.450 0. 131 0.251 -7.921 0.073 0. 108 0.450 0.056 0.052 0.450 0.733 1.798 0.450 0. 112 0.033 0.450 0. 191 0.088 0.450 0.208 0.291

03C 0. 0 0. 136 0. 119 0.449 0. 131 0. 258 -3.021 0. 085 0.098 0. 449 0. 057 0.051 0. 449 0.646 1. 902 0. 449 0. 112 0. 031 0. 449 0. 187 0.076 0. 449 0. 209 0. 289

03D 0.0 0. 13" 0. 121 0.450 0. 135 0.253 -7.937 0.073 0. 114 0.450 0.056 0.052 0.450 0.736 ... 0.450 0. 113 0.030 0.450 0. 196 0.091 0.450 0.201 0.288

Final Sequence 0.0 0.086 0.089 0.449 0. 126 0.239 -1.000 0. 055 0. 103 0.449 0.049 0.047 0.449 0.589 1. 743 0.449 0.082 0.033 0.449 0. 141 0.071 0.449 0. 192 0.281

04A 0.0 0. 127 0. 109 0.450 0. 128 0. 244 -3.019 0.079 0. 103 0.450 0.056 0.051 0.450 0.635 1.898 0.450 0. 106 0.031 0.450 0. 183 0.080 0.450 0. 216 0.286

04B 0.0 0. 130 0. 116 0.450 0. 132 0.249 -7.934 0.074 0. 114 0.450 0.056 0.052 0.450 0.746 1.785 0.450 0. 109 0.031 0.450 0. 188 0.088 0.450 0.206 0.287

04C 0. 0 0. 137 0. 128 0. 449 0. 134 0. 258 -3. 021 0. 07 3 0. Ill 0. 449 0.056 0.05 3 0. 449 0. 662 1. 883 0. 449 0. Ill 0.031 0. 449 0. 187 0. 084 0.449 0. 218 0.296

04D 0.0 0. 138 0. 123 0.448 0. 135 0.259 -7.938 0.076 0. 113 0.448 0.055 0.053 0.448 0. 774 ... 0.448 0. 112 0.032 0.448 0. 192 0.092 0.448 0. 207 0.290

Final Sequence 0.0 0.088 0. 092 0.450 0. 127 0.241 -0.977 0.056 0. 106 0.450 0.051 0.044 0.450 0.604 1.737 0.450 0.084 0.032 0.450 0. 142 0.066 0.450 0. 197 0.289

05A 0.0 0. 123 0. 106 0.446 1.718 0.431 -1.001 0.088 0.086 ... — ... — ... ... ... ... .__ ... ... ... Final Sequence 0.0 0.090 0.089 0.4S0 0. 126 0.238 -1.000 0.057 0. 101 0.450 0. 053 0.048 0.450 0.475 1. 650 0.450 0.078 0.038 0.450 0. 153 0.081 0.450 0. 168 0.282

06A 0.0 0. 119 0. 103 0.450 0. 118 0. 246 -7.938 0.093 0. 099 0.450 0.056 0.051 0.450 0. 537 1.761 0. 450 0. 107 0. 038 0.450 0. 188 0.084 0.450 0. 202 0. 296

06B 0.0 0. 128 0. 114 0.451 0.129 0.242 -7.939 0.081 0. 115 0.451 0.057 0.051 0.451 0.664 1.743 0.451 0. 117 0.033 0.451 0.207 0. 106 0.451 0.211 0.288

06C 0.0 0. 123 0. 112 0.448 0. 125 0. 251 -3.022 0.085 0.116 0.448 0.059 0.055 0.448 0. 556 1. 797 0.448 0. 118 0.039 0,448 0. 168 0. 101 0.446 0.217 0.298

06 D 0.0 0. 132 0. ill 0.448 0. 127 n. Ml -7.936 0.084 0. 11» 0. 448 0.058 0.053 0.448 0.648 1.787 0.448 0. 118 0.036 0.448 0.212 0. 104 0.448 0.213 0.283

06E 0.0 0. 133 0. Ill 0.449 0. 124 0.251 -7.938 0.082 0.118 0.449 0.058 0. 052 0.449 0.565 1 0.449 0. 116 0.035 0.449 0.203 0. 108 0.449 0.203 0.291

Final Sequence 0.0 0,092 0.083 0.448 0. 126 0. 237 -0.998 0.047 0. 092 0.448 0.052 0,047 0.448 0.480 1. 646 0. 448 0.088 0.037 0.448 0. 154 0. 079 0. 448 0. 195 0. 280

Notes: 1. All valve signal times are referenced to tg. 2. Valve delay time is the time required for initial valve movement after the valve "open" or "closed" solenoid has been energixed. 3. Final sequence check is conducted without propellants and within 12 hr before testing. 4. Data reduced from oscillogram. m

?

TABLE VII (Concluded)

tS3 CO

Firing Number J4-1901-

Shutdown

Main Fuel Valve Main Oxidizer Valve Gas Generator

Fuel Poppet Gas Generator

Oxidizer Poppet Oxidizer Turbine

Bypass Valve

Time of

Closing Signal


Valve Closing Time,

sec

Time of

Closing Signal


Valve Closing Time,

sec

Time of

Closing Signal


Valve Closing Time, sec

Time of

Closing Signal


Valve Closing Time,

sec

Time of

Opening Signal

Valve Delay Time,

sec

Valve Opening Time, sec

03A 32.573 0. 108 0. 302 32. 573 0.086 0. 183 32.573 0.068 0.013 32.573 0.032 0.013 32.573 0.251 0.518

03B 7. 586 0.099 0. 290 7. 586 0.078 0. 176 7. 586 0.075 0. 016 7.586 0.036 0.015 7.586 0.234 0.486

03C 32. 573 0. Ill 0. 330 32. 573 0.088 0. 184 32.573 0.069 0.015 32.573 0.031 0.015 32.573 0.252 0.513

03D 1. 263 0.096 0.295 1. 263 ... 1.263 0.081 0. 020 1.263 0.041 0.018 1. 263 0. 158 0.504

Final Sequence 4. 704 0.081 0. 224 4. 704 0.053 0. 123 4. 704 0.090 0.037 4. 704 0.061 0. 022 4. 704 0.218 0.574

04A 25.020 0. 107 0. 301 25.020 0. 081 0. 176 25.020 0. 068 0. 014 25.020 0.031 0.013 25.020 0.247 0.543

04B 7.586 0. 101 0. 294 7. 586 0. 076 0. 174 7.586 0.074 0. 015 7.586 0.036 0. 015 7.586 0. 217 0.492

04C 32.573 0. 108 0. 315 32.573 0.086 0. 186 32.573 0.069 0.015 32.573 0.031 0.014 32.573 0. 249 0.528

04D 1.994 0.096 0.293 1.994 --- --- 1.994 0.076 0.016 1.994 0.036 0.014 1.994 0. 198 0.499

Final Sequence 6.447 0.081 0.224 6.447 0.062 0. 121 6.447 0.094 0.037 6.447 0.061 0.024 6.447 0. 222 0.588

05A 0.448 0.098 0.271 ... --- ... ... --- --- ... ... ... ... ... --- Final Sequence 4.634 0.079 0. 226 4. 634 0.053 0. 123 4.634 0. 092 0. 034 4.634 0.059 0. 026 4.634 0. 218 0. 578

06A 32.573 0. 107 0.313 32.573 0.083 0. 178 32.573 0.066 0.012 32.573 0.031 0.013 32.573 0. 254 0.574

06B 7.588 0. 103 0.316 7.588 0.078 0. 174 7.588 0.074 0.016 7.588 0.036 0.015 7.588 0.233 0.525

06C 32.571 0.121 0. 365 32.571 0.089 0. 191 32.571 0.074 0.015 32.571 0.033 0.014 32.571 0. 276 0.616

06D 7.584 0. 109 0.341 7.584 0.081 0. 179 7.584 0.079 0.016 7.584 0. 037 0.015 7.584 0. 245 0.522

06E 1.247 0. 109 0.347 1. 247 1. 247 0.087 0.026 1.247 0. 051 0. 022 1.247 0. 169 0.564

Final Sequence 6.695 0.079 0.222 6. 695 0.064 0. 118 6.695 0.093 0.037 6.695 0.059 0.026 6.695 0.218 0.576

n

Notes: 1. All valve signal times are referenced to to. 2. Valve delay time is the time required for initial valve movement after the valve "open" or "closed" solenoid has been energized. 3. Final sequence check is conducted without propellants and within 12 hr before testing. 4. Data reduced from oscillogram.

TABLE VIII ENGINE PERFORMANCE SUMMARY

to CO

Firing Number J4-1901- 03A 03C 04C 06A 06C

Site Normalized Site Normalized Site Normalized Site Normalized Site Normalized

Thrust, lbf 230,597 227,639 229,956 227, 390 229,450 226, 787 229,959 227, 274 230,360 227, 645

Chamber Pressure, psia 788.9 775. 1 786.8 774.4 785.5 772.4 787.4 773.9 788.6 775.4 Overall Engine Performance

Mixture Ratio 5.496 5 ">07 5.564 5.574 5. 583 5.597 5.606 5.621 5.638 5. 619

Fuel Weight Flow, lbm/sec 84.11 82.57 83.25 81. 87 82.76 81.27 82.59 81. 07 82.54 81.37

Oxidizer Weight Flow, lbm/sec 462.3 454.7 463.2 456.4 462. 0 454.9 463. 1 455.7 465. 3 457.2

Total Weight Flow, lbm/sec 546.4 537. 3 546.5 538. 3 544.8 536. 2 545.6 536.8 547.9 538.6

Thrust Mixture Ratio 5.701 5. 715 5. 773 5. 787 5.788 5.806 5.818 5. 837 5. 849 5.832

Chamber Total Weight Flow, lbm/sec 539. 3 530.2 539.4 531.2 537.8 529.2 538.6 529.8 540.8 531.6 Performance

Characteristic Velocity, ft/sec 8017 8011 7994 7989 8005 7999 8012 8005 7992 7995

Pump Efficiency, percent 73.8 73.8 73.8 73.8 73.7 73.7 73.9 73.9 74.0 74.0

Fuel Turbopump

Pump Speed, rpm 26,829 26,573 26,640 26, 449 26,518 26, 319 26,529 26,329 26, 671 26,478

Turbine Efficiency, percent 60.8 60.6 60.3 60.2 59.4 59.2 59.4 59.2 59.4 59.3

Performance Turbine Pressure Ratio 7. 38 7.38 7.30 7.29 7.33 7.33 7. 34 7.34 7.33 7. 33

Turbine Inlet Temperature, °F 1230 1210 1230 1214 1273 1256 1242 1225 1261 1239

Turbine Weight Flow, lbm/sec 7. 11 7.03 7.08 7.01 7.02 6.94 7.07 6.98 7.08 7.00

Pump Efficiency, percent 80. 3 80.2 80. 3 80.3 80. 3 80. 3 80. 3 80.3 80.4 80. 3

Oxidizer Turbopump

Pump Speed, rpm 8707 8633 8724 8650 8695 8620 8673 8602 8702 8624

Turbine Efficiency, percent 48.4 48.2 48.7 48.4 49.2 48.9 48.9 48.7 49.1 48.9

Performance Turbine Pressure Ratio 2.58 2.58 2.60 2.59 2.59 2.58 2.59 2.59 2.58 2. 58

Turbine Inlet Temperature, °F 827.4 813. 3 831.6 819.7 843. 7 832.0 832.9 821.1 847.5 831.4

Turbine Weight Flow, lbm/sec 6.23 6.16 6. 19 6. 13 6. 14 6.07 6.18 6. 11 6.19 6. 13

Gas Generator Mixture Ratio 0.957 0.946 0.957 0.948 0.983 0.973 0.964 0.955 0.976 0.963

Performance Chamber Pressure, psia 691. 3 681.4 688.0 679. 2 686. 6 677. 2 688.0 678. 3 691.2 681.6

Notes: 1. Site data are calculated from test data. 2. Normalized data are corrected to standard pump inlet and engine ambient pressure conditions. 3. Input data are test data averaged from 29 to 30 sec, except as noted. 4. Site and normalized data were computed using the Rocketdyne PAST 640 modification zero computer program.

o o

OJ CO

AEDC-TR-68-238

APPENDIX Ml

INSTRUMENTATION

The instrumentation for AEDC tests J4-1901-03 through J4-1901-06 is tabulated in Table IJI'l. The location of selected major engine instrumentation is shown in Fig. 111 = 1.

130

ÄEDCTR-68-238

TABLE 111-1

INSTRUMENTATION LIST

AEDC Code Parameter

Current

ICC Control

I1C, Ignition

Event

Tap No, No. Range

Micro- sacic

Magnetic Tape

Oscillo- graph

Strip Chart

X-Y Plotter

EASIOV

EECL

EECO

EES

EFBVC

EFPVC/O

EHCS

EID

EI PCS

EMCS

EMP-1

EMP-2

EOBVC

EOPVC

EOPVO

ESTDCS

RASIS-1

RASIS-2

RGGS-1

RGGS-2

QF-1A

QF-2

QF-1SAM

QFRP

QO-1A

QO-2

QORP

LFVT

LGGVT

LOTBVT

LOVT

LPUTOP

LSTDVT

Augmented Spark Igniter Oxirf:zer Valve

Engine Cutoff Lockin

Engine Cutoff Signal

Engine Start Command

Fuel Bleed Valve Closed Limit

Fuel Prevalve Closed/Open Limit

Helium Control Solenoid

Ignition Detec-.ed

Ignition Phase Control Solenoid

Main-Stage Control Solenoid

Main-Stage Pressure No. 1

Main-Stage Pressure No. 2

Oxidizer Bleed Valve Closed Limit

Oxidizer Prevalve ClosedLimit

Oxidizer Prevalve Open Limit

S:art Tank Discharge Control Solenoid

Augmented Spark Igniter No. 1

Augmented Spark Igniter No. 2

Gas Generator Spark No. 1

Gas Generator Spark No. 2

Flews

Fuel

Fuel

Fuel Flow Stall Approach Monitor

Fuel Reclrculation

Oxidizer

Oxidizer

Oxidizer Reclrculation

Position

Main Fuel Valve

Gas Generator Valve

Oxidizer Turbine B;-pass Valve

Main Oxidizer Valve

Propellant Utilization Valve

Start Tank Discharge Valve

PPF

PFFA

POF

POFA

amp

0 to 30

0 to 30

Open/Closed

On /Off

On/Off

On/Off

Open/Closed

Closed/Open

On/Orf

On/OK

On/Off

On/Off

On/Off

On/Off

Open /Closed

Closec

Open

On/Off

On/Off

On/Off

On/OH

On/Off

gpm

0 to 9000

0 to 90:0

0 to 9000

0 to 160

0 to 3000

0 to 3000

0 to 50

Percent Open

0 to 100

0 to 100

0 to 100

0 to 100

0 to 100

0 to 100

131

AEDC-TR-68-238

TABLE lll-l (Continued)

AEDC Code Parameter

Pressure

PA". Test Cell

PA 2 Test Cell

PA 3 Tea* Coil

PC-IP Thrust Chamber

PC-3 Thrust Chamber

PCBO- 1 Constant Bleed Orifice

PC DP Crossover Duct Pjrge

PCGG-1P Gas Generator Chamber

PCGG-2 Gas Generator Chamber

PTBL Fuel Bleed Line

PFJ-1A Main Fuel Injection

PFJGG-1A Gas Genciator Fuel Injection

PFJGG-2 Gas Generator Fuel Injection

PFPC-1A Fuel Pump Balance Piston Cavity

PFPD-1P Fuel Pump Discharge

PFPD-2 Fuel Pump Discharge

PFPI-1 Fuel Pump Ir.le;

PFP1-2 Fuel Pump Inlet

PFP1-3 Fjel Pump Inlet

PFPPSD-1 Fuel Pump Primary Seal Drain

PFHPO Fuel RccircLla-.ion Pump Outlet

PFHPR Fuel Recirculation Pump Return

PFST-1P Fuel Start Tank

PFST-2 Fuel Start Tari

PFÜT Fuel Tank Ullage

P7VI ruel Tan* Press.irization Line Nozzle Inlet

Tap No.

CGI

CGI A

GG1A

CF2

GF4

GF4

PF5

PF3

PF2

TF1

TF1

PFVL Fuel Tar.k Prcssurization Line Nozzle Throa:

PHECMO Pneumatic Control Module Outlet

PHEOP Oxicizer Recirculation Pump Purge

PHET-1P Helium Tank XNi

PHFT-2 Helium Tank NN1

P1IRO-1A Helium Regulator Outlet NX2

POJ-1A Main Oxicizer Injection C03

POJ-2 Main Oxinizer Injection C03A

POJ-3 Main Oxidizcr Injection

POJGG-1A Gas Generator Oxidizer Injection GOS

POJGG-2 Gas Generator Oxidizer Injection G05

POPBC-1A Oxidizer Pump Bearing Coolant P07

Range

psia

0 to 0. 5

0 to 1.0

U to 5. 0

0 to 1000

0 to 1000

0 to 50

0 to 100

0 to 1000

0 to 1000

0 to 5001

0 to 1000

0 to 1000

0 to 1000

0 to 1000

0 to 1500

0 to 1900

0 to 100

0 to 100

0 to 200

0 to 200

0 to 60

0 to 30

0 to 1500

0 to 1500

0 to 100

0 to 1000

0 to 1000

0 to 750

0 TO 150

0 to 3500

0 to 3500

0 -JO 750

0 to 1000

0 to 1003

0 to 2000

0 to 1000

0 to 1000

0 to 500

Micro- sadic

Magnetic Oscillo- Strip X-Y Tape graph Chart Plotter

132

AEDC-TR-68-238

TABLE UM (Continued)

AEDC Code Parameter

Pressure

Tap No. Range

psla

Micro- Magnetic sadic Tape

POFD-1P Oxidlzer Pump Discharge P03 0 to 1500 X

P0PD-2 Oxidlzer Pump Discharge P02 0 to 1500 X X

POPI-1 Oxidlzer Pump Inlet 0 to 100 X

POPI-2 Oxidizer Pump Inlet 0 to 200 X

POP1-3 Oxidlzer Pump Inlet 0 to 100

POPSC-1A Oxidizer Pump Primary Seal Cavity

POS OtoSO X

PORPO Oxidizer Recirculation Pump Outlet

0 to 115 X

PORPR Oxidizer Recirculation Pump Return

0 to 100 X

POT1-1A Oxidlzer Turbine Inlet TG3 0 to 200 X

POTO-1A Oxidizer Turbine Outlet TG4 0 to 100 X

POUT Oxidizer Tank Ullage 0 to 100 X

POVCC Main Oxidizer Valve Closing Control

0 to 500 X

POVI Oxidizer Tank Press urizatlon Line Nozzle Inlet

0 to 1000 X

POVL Oxidizer Tank Pressurization Line Nozzle Throat

0 to 1000 X

PPUVI-1A Propellant Utilization Valve Inlet POS 0 to 1500 X

PPUVO-1A Propellant Utilization Valve Outlet : P09 0 to 500 X

PTCFJP Thrust Chamber Fuel Jacket Purge

0 to 100 X

PTCP Thrust Chamber Purge 0 to 1000 X

PTPP Turbopump and Gas Generator Purge

Speeds

0 to 250

rpm

X

NFP-1P Fuel Pump PFV 0 to 30, 000 X X

NFRP Fuel Recirculation Pump 0 to 15, 000 X

NOP-IP Oxidizer Pump POV 0 to 12.000 X X

NORP Oxidlzer Recirculation Pump

Temperatures

Oto 15,000

•F

*

TA1 Test Cell (North) -50 to +800 X

TA2 Test Cell (East) -50 to +800 X

TA3 Teat Cell (South) -50 to +800 X

TA4 Test Cell (West) -50 to +800 X

TAIP-1A Auxiliary Instrument Package -300 to +200 X

TAIPAA Auxiliary Instrument Package Area Ambient

-200 to +500 X

TCDP Crossover Duct Purge -150 to+150 X

TECP-1P Electrical Controls Package NST1A -300 to +200 X

TEHAA Engine Handler Attach Area -200 to +500 X

OBCüIO- Strip X-Y graph Chart Plotter

Ambien*

133

AEDC-TR-68-238

TABLE 111-1 (Continued)

AEDC Code Parameter

Temperatures

Tap No. Range

•F

Micro- sadic

Magnetic Oscillo- Strip Tape graph Chart

X-Y Plotter

TFASIL-2 Augmented Spark Igniter Fuel Line Skin

-400 to +300 X

TFASIL-4 Augmented Spark Igniter Fuel Line Skin

-425 to +500 X

TFBV-1A Fuel Bleed Valve GFT1 -425 to -375 X

TFD-1 Fire Detection 0 to 1000 X X

TFDAA Fuei Hign Preaejre Dact Area Ambient

-200 to +503 X ■

TFJ-1P Main Fuel Injection CFT2 -425 to +250 X X

TFJ-22 Main Fuel Injection -450 to +250 X

TFPD-1P Fuel Pump Discharge PFT1 -425 to -400 X X X

TFPD-2 Fuel Pump Discharge PFT1 -425 to -400 X

TFP1-1 Fuel Pump Inlet -425 to -400 X X

TFPI-2 Fuel Pump Inlet -425 to -400 X X

TFRPO Fuel Recirculation Pump Outlet -425 to -350 X

TFRPR Fjel Recirculation Pump Return Line

-425 to -250 X '

TFRT-1 Fuel Tank -425 to -410 X i

TFRT-3 Fuel Tank -425 to -410 X

TFST-1P Fuel Start Tank TFT1 -350 to +100 X

TFST-2 Fuel Start Taiu TFT1 -350 to +100 X X

TFTD-2 Fuel Turbine Discharge Duct -200 to -1000 X X

TFTD-3 Fuel Turbine Discharge Duct -200 to +1000 X X

TFTD-4 Fuel Turbine Discharge Duct -200 to +1000 X x2

TFTD-8 Fuel Turbine Discharge Duct -200 to +1400 X X

TFTO Fuel Turbine Outlet TFT2 0 to 1800 X

TFTSD-1 Fuel Turbine Seal Drain Line -300 to+100 X

TGGO-1A and 2 Gas Generator Outlet GGT1 0 to 2500 X X X

TGGVRS Gas Generator Valve Retaining Screw

-100 to +100 X x3

THET-1P Helium Tank NNT1 -350 to +100 X X

TNODP Oxidizer Dome Purge 0 to +300 X

TOAS1L-1 Augmented Spark Igniter Oxidizer Line Skin

-423 to -500 X

TOASIL-2 Augmented Spark Igniter Oxidizer Line Skin

-400 to +300 X

TOBS-1 Oxidizer Bootstrap Line -300 to +250 X

TOBS-2 Oxidizer Bootstrap Line -300 to+250 X

T0BS-2B Oxicizer Bootstrap Line -300 to +250 X

T0BV-1A Oxidizer Bleed Valve GOT2 -300 to -250 X

TOD A A Oxidizer Dome Area Ambient -200 to +500 X

TODS-1 Oxidizer Dome Skin -300 to +100 X X

TODS-2 Oxidizer Dome Skin -300 to +100 X X4

134

AEDC-TR-68-238

TABLE lll-l (Continued)

AEDC Code Parameter

Tap No. Range

Micro- sadic

Magnetic Oscillo- Strip Ta» graph Chart

X-Y Plotter

i Temperatures •F

TOPB-1A OxLdizer Pump Bearing Coolant POT4 -300 to -250 X

TOPD-1P Oxldizer Pump Discharge POT3 -300 to -250 X X XX

TOPD-2 Oxidizer Pump Discharge POT 3 -300 to -250 X

TOPI-1 Oxldizer Pump Inlet -310 to -270 X X

TOP1-2 Oxidizer Pump Inlet -310 to -270 X X

TORPO Oxldizer Recirculation Pump Outlet

-300 to -250 X

TOHPR Oxidizer Recirculation Pump Return

-300 to -140 X

TORT-1 Oxldizer Tank -300 to -287 X

TORT-IB Oxidizer Tank -300 to -287 X

TORT-3 Oxidizer Tank -300 to -287 X

TOT1-1P Oxidizer Turbine Inlet TGT3 -300 to 1200 X X

TOTO-IP Oxidizer Turbine Outlet TCT4 0 to 1000 X

TOVL Oxldizer Tank Pressurlzatlon Line Nozzle Throat

-300 to +100 X

TPIP-1P Primary Instrument Package -300 to +200 X

TPIPAA Primary Instrument Package Area Ambient

-200 to +500 X

TSC2-1 Thrust Chamber Skin -300 to +500 X

TSC2-1Z Thrust Chamber Skin -300 to +500 X

TSC2-13 Thrust Chamber Skin -300 to +500 X X

TSC2-17 Thrust Chamber Sicin -300 to +500 X



TSOVC-1 Oxldizer Valve Actuator Cap -325 to + 150 X X

TSTDVAA Start Tank Discharge Valve Area Ambient

-200 to +500 X

TSTDVDL Start Tank Discharge Valve Drain Line

-100 to +200 X

TSTDVOC Start Tank Discharge Valve Opening Control Port

-300 to +200 X x3

TTC-1P Thrust Chamber Jacket (Control)

CS1 -425 to +500 X X

TTC-2 Thrust Chamber Jacket -425 to + 100 X

TTCP5 Thrust Chamber Purge -346 to -504 X

TTPP Turbopump Purge -150 to+150 X X

135'

AEDC-TR-68-238

TABLE UM (Concluded)

AEDC Cade Parameter

Vibratior.9

UAS1F-1 Augmented Spark Igniter Fuel Orifice Block Tangential

UAS1V-1 Augmented Spark Igniter Oxidizer Valve Axial

UASIV-3 Augmented Spark Igniter Oxidizer Valve Tangential

UFPR Fuel Pump Radial 90 deg

UMFV-1 Mair. Fuel Valve Radial

UMFV-3 Main Fuel Valve Tangential

UOPR Oxidizer Pump Radial 90 deg

UOTBV-1 Oxidizer Turbine Bypass Valve Axial

UTCD-1 Thrust Chamber Dome




U1V3C No. 1 Vibration Safety Counts

U2VSC No. 2 Vibration Safety Counts

U3VSC Xo. 3 Vibration Safety Counts

Voltage

VCB Control Bus

VIB Ignition Bus

VI DA Ignition Detect Amplifier

VPUTEP Propellant Utilization Valve Excitation

Tap No. Range

±150

±130

±150

±300

±150

±150

±200

±150

±500

±500

±500

xlOOO

On I Off

On/Off

On/Off

volte

0 to 36

0 to 36

9 to 16

0 to 5

Micro- sadic

Magnetic Tape

Oscillo- Strip X-Y graph Char: Plotter

Notes: 1. Range changed from Oto 100 psia beginning with test 04 2. Added beginning with test 04 3. Deleted beginning with test 05 4. Added beginning with test 05 5. Added beginning with test 06

136

CO

HE«T EXCHANGER

a. Engine Pressure Tap Locations

Fig. 111—1 Instrumentation Locations

> m o n H TO

> m o o

MAIN OXID LIN£ '

GO oo

MEAT EXCHANGER

FUEL BLEED VALVE

TFBV-IA

►o w 00

b. Engine Temperature, Flow, and Speed Instrumentation Locations

Fig. Ill-l Continued

TSOVC-1

oo CD

inlet Port

Sequence Outlet

c. Main Oxidizer Valve

Fig. Ill-l Continued

m o n

AEDC-TR-68-238

TSTDVOC

Four-Way Valve

d. Start Tank Discharge Valve Fig. Ml-l Continued

140

OXIDIZER BÜEO

VALVE

T 2.5

7?

V

-TOBS-2B

TTTT 3XXE

TOBS-2

ALL DIMENSIONS IN INCHES o. Gas Generator Qtidrxer Supply Liiw

Fig. Mil Continued

> m o ■ H 71 i

IO u 00

TURBINE EXHAUST MANIFOLD

INS

TSC2-I

TUBE 473

TUBE 422

TUBE 362

TUBE 341

TSC2-I3

VIEW LOOKING AFT f. Thrust Chamber

Fig. II1-1 Concluded

HATBANDS

0 K-—EXIT PLANE

-TSC2-I7

TUBE 206

> m o n ■ -t TO ■

GO ■ M

AEDC-TR-68-238

APPENPIX IV

METHOD OF CALCULATION (PERFORMANCE PROGRAM)

TABLE IV-1 PERFORMANCE PROGRAM DATA INPUTS

1

2

3

4

:7

8

9

10

11

12

13

14

15

16

17

Thrust Chamber (Injector Face) Pressure, psia

Thrust Chamber Fuel and Oxidizer Injection Pressures, psia

Thrust Chamber Fuel Injection Temperature, °F

Fuel and Oxidizer Flowmeter Speeds, Hz

Fuel and Oxidizer Engine Inlet Pressures, psia

Fuel and Oxidizer Pump Discharge Pressures, psia

Fuel and Oxidizer Engine Inlet Temperatures, °F"

Fuel and Oxidizer (Main Valves) Temperatures, 9F

Propeilant Utilization Valve Center Tap Voltage, volts

Propellant Utilization Valve Position, volts

Fuel and Oxidizer Pump Speeds, rpm

Gas Generator Chamber Pressure, psia

Gas Generator (Bootstrap Line at Bleed Valve) Temperature, °F

Fuel* and Oxidizer Turbine Inlet Pressure, psia

Oxidizer Turbine Discharge Pressure, psia

Fuel and Oxidizer Turbine Inlet Temperature, °F

Oxidizer Turbine Discharge Temperature, °F

gas ♦At AEDC, fuel turbine inlet pressure is calculated from generator chamber pressure.

143

AEDC-TR-68-238

NOMENCLATURE

A Area, in.2

B Horsepower

C Coefficient

c* Characteristic velocity, ft/sec

D Diameter, in.

F Thrust, lbf

H Head, ft

h Enthalpy, Btu/lbm

I Impulse

M Molecular weight

N Speed, rpm

P Pressure, psia

Q Flow rate, gpm

R Resistance, sec2/ft3-in.2

r Mixture ratio, O/F

T Temperature, °F

TC* Theoretical characteristic velocity, ft/sec

W Weight flow, lb/sec

z Differential pressure, psi

ß Ratio

7 Ratio of specific heats

n Efficiencies

6 Degrees

P Density, lb/ft3

SUBSCRIPTS

A Ambient

AA Ambient at thrust chamber exit

B Bypass nozzle

144

A EDC-T.R -68-238!

BIR Bypass nozzle inlet (Rankine)

BNI Bypass nozzle inlet (total)

C Thrust chamber

CF Thrust chamber, fuel

CO Thrust chamber, oxidizer

CV Thrust chamber, vacuum

E Engine

EF Engine fuel

EM Engine measured

EO Engine oxidizer

EV Engine, vacuum

e Exit

em Exit measured

F Thrust

FM Fuel measured

FV Thrust, vacuum

f Fuel

.G Gas generator

GF Gas generator fuel

GO Gas generator oxidizer

HI Hot gas duct No. 1

H1R Hot gas duct No. 1 (Rankine)

H2R Hot gas duct No. 2 (Rankine)

IF Inlet fuel

IO Inlet oxidizer

ITF Isentropic turbine fuel

ITO Isentropic turbine oxidizer

N Nozzle

NB Bypass nozzle (throat) .

145

AEDC-TR-68-238

NV Nozzle, vacuum

O Oxidizer

OC Oxidizer pump calculated

OF Outlet fuel pump

OFIS Outlet fuel pump isentropic

OM Oxidizer measured

OO Oxidizer outlet

PF Pump fuel

PO Pump oxidizer

PUVO Propellant utilization valve oxidizer

RNC Ratio bypass nozzle, critical

SC Specific, thrust chamber

SCV Specific thrust chamber, vacuum

SE Specific, engine

SEV Specific, engine vacuum

T Total

TEF Turbine exit fuel

TEFS Turbine exit fuel (static)

TF Fuel turbine

TIF Turbine inlet fuel (total)

TIFM Turbine inlet, fuel, measured

TIFS Turbine inlet fuel isentropic

TIO Turbine inlet oxidizer

TO Turbine oxidizer

t Throat

V Vacuum

v Valve

XF Fuel tank repressurant

XO Oxidizer tank repressurant

146

AEDC-TR-68-238

PERFORMANCE PROGRAM EQUATIONS

THRUST

Thrust Chamber, Vacuum

Fcv = C (Pc)a + B (Pc) + A

Empirical Determination from Curve Fit of Thrust versus Pp

Thrust Chamber FC = FcV - PAAAe

Ae = Aera + 12.8

PAA = Measured Cell Pressure

Engine, Vacuum

Engine

MIXTURE RATIO

FEV = Fcv

FE = FC

Engine

Thrust Chamber

WEO TE =

WEF

WEO = WOM - Wxo

WEF = WFM - WXF

re •Weo WCF

Weo = WOM - Wxo - WGO

WCF = WFM - WxF - WGF

WxO = Standard 0.9 lb/sec

WXF = Standard 2.1 lb/sec

WGO . WT - WGF

WGF 1+rp,

WT PTIF ATIF K7

TC*TIF

K7 = 32.174

147

AEDC-TR.68-238

Normalized engine and thrust chamber vacuum data calculated as measured, except all flows are normalized using standard inlet pressures, temperatures, and densities listed below:

PlO STD = 39 psia

PlFSTD = 30 psia

pl0 STD = 70.79 lb/ftJ

pIF STD = 4.40 lb/ft»

TioSTD = -295.2°F -..;;.,

TIFSTD = 422.5°F

SPECIFIC IMPULSE

Engine FE ISE = -=r

Engine, Vacuum

WE

WE = WEO + WEF

ISEV + K'EV

WEV = "E Normalized using standard inlet pressures, temperatures, and densities

Chamber Fc he =

Chamber, Vacuum

ffc

WC = Wco + WCF

Iscv = |£J-

W'cv ~ Wc Normalized using standard inlet pressures, temperatures, and densities

CHARACTERISTIC VELOCITY

Thrust Chamber c* _ Ei *s A>

K7 = 32.174

Thrust Chamber, Vacuum

K? Pcv At C*v = v wcv

K7 = 32.174

148

AEDC-TR-68-238

i Nozzle r>-:v: °*-*

K6 = 1.086

Nozzle, Vacuum

LNV - x

THRUST COEFFICIENT

Engine

Engine, Vacuum

DEVELOPED PUMP HEAD

Oxidizer

CF =

CFV =

K6 = 1.086

_Fc PcAt

1 cv PnA CAt

»°-*>fä-m

Fuel

K4 = 144

p = National Bureau of Standards Values f(P,T)

HF = 778.16 AhoFIS

AhoFIS = hoFIS - hlF

h0FIS = f(P,T)

hlF = f(P,T)

Fuel and Oxidizer Vacuum

Conditions normalized using standard inlet pressures, temperatures, and densities.

PUMP EFFICIENCIES

Fuel, Isentropic hOFIS - hlF

^F hoF ~ *>IJT

h0F ■ f(P0F, TQF)

149

AEDC-TR-68-238

Oxidizer, Isentropic

Yo = 1.000 K40 = -5.053 K50 = 3.861 K60 = 0.0733

TURBINES

Oxidizer, Efficiency BT0

,T0 ~ ^Fo~

n™ K ffpo Ho BTO =.K5 —

K5 = 0.001818

Wpo = WOM + W PUVO

WPUVO ->/Zppv,° P0°

Zpuvo = A + B (Poo) A = -1597

B - 2.3828

if POO > 1010

set Poo = 1010 Öpuvo

r gpuvoT + F [(e) 7 J

£n Rv = A + B (öpuvo) + C(ÖPUVO)' + D (e) öpuvo r ^PUVOI

2

+ E 0PUVO (e) '

A = 5.566 x 10"l

B = 1.500 x 10~2

C = 7.941 x 10~6

D = 1.234 E = -7.255 x 10-2

F = 5.069 x 10-2

Fuel, Efficiency BTF

Vjf BlTF

150

AEDC-TR-68-238

BiTF = K10 AhF WT

AhF = hTIF - liTEF

BTF . BPr. KS (aj-St)

WpF = WFM

k10 = 1.415

Ks = 0.001818

Oxidizer, Developed Horsepower

BTO = Bpo

Bpo /WPO_HO\

K5 = 0.001818

Fuel, Developed Horsepower

BTF = BPF

■"-*•(■**=«) '

WpF = WFM

Fuel, Weight Flow

WTF = WT

»TO = ffT - WB

r2K7 y * T r yH2-n* WB * lyH2-t (pRN^ y«2 J [i - (PRNC) yH2 J

ANB PBNI

(HHajBia)"

PHNC = f (/3NB. yH2)

0NB = DNB/DB

yH2- MH2 = f(TH2R. fG)

ANB = K13(DNB)2

Kn = 0.7854

TBIR = T-riO + 460

PßNl = PTEFS

PTF.FS = Iteration of PTEF

151

AEDC-TR-68-238

PTEF PTEFS

Ke = 38.90

1 + Kg / W

\PTE]

T

FS

TH2H

D*TEF N1H2

7R2

GASGENERATOR

Mixture Ratio

rG = D, (THi)3 + Cx (THI)2 + Bj (THI) + Ax

Aj = 0.2575 *'■"■■< ■■ " -'-

Bt = 5.586 x 10-*

Cj = -5.332 x 10-»

Dj = 1.1312 x 10"u

THI = TTIFM

Flows

TC*TIF = D2(THI)3 + C2(THI)

2 + B2(THI) ■+ A2

A2 = 4.4226 x 103

B2 = 3.2267

C2 = -1.3790 x IG"3

D2 = 2.6212 x 10-7

i + *J WT Y \PTIFS/

THlR D*TIF MHI YHI _

Yni

PTIF = PTIFS ym-i

K8 = 38.8983

Note: PTIF >S determined by iteration.

THIR = TTIFM + 460

MHI, yHl,Cp,rHl = f (THIR.TG)

152

UNCLASSIFIED Security Classification

DOCUMENT CONTROL DATA -R&D (Security clasaillcatton of title, body of abstract and indexing annotation must be entered when the overall report la elaaalllad)

I. ORIGINATING ACTIVITY (Corporate author) Arnold Engineering Development Center ARO, Inc., Operating Contractor Arnold Air Force Station, Tennessee

2a. REPORT SECURITY CLASSIFICATION

UNCLASSIFIED 2b. CROUP

N/A 3. REPORT TITLE

FLIGHT SUPPORT TESTING OF THE J-2 ROCKET ENGINE IN PROPULSION ENGINE TEST CELL (J-4) (TESTS J4-1901-03 THROUGH J4-1901-06)

«. DESCRIPTIVE NOTES (Type of report and Inclusive dates)

July 23 through August 15, 1968 - Interim Report 8. AJTHOBI5I (First name, middle Initial, laat name)

N: R. Vetter, ARO, Inc.

6- REPORT DATE

December 1968 7a. TOTAL NO. OF PAGES

161 7b. NO. OF REFS

Sa. CONTRACT OR GRANT NO.

b. PROJECT NO. 9]_94

System 92IE

F40600-69-C-0001 Sa. ORIGINATOR'S REPORT, NUMBER(S) 8R T, .N U

AEDC-TR-68-238

9b. OTHER REPORT NO(S) (Any other numbers that may be assigned thta report)

N/A

10. DISTRIBUTION STATEMENT

of Defense must -J),

fTTsu PPLEMENTARY NOTES

Available in DDC,

12. SPONSORING MILITARY ACTIVITY

NASA, Marshall Space Flight Center (I-E-J), Huntsville, Alabama 35812

13 ABSTRACT

Fourteen firings of the Rocketdyne J-2 rocket engine (S/N J-2036-1) were conducted at pressure altitude conditions during four test periods (J4-1901-03 through J4-1901-06) between July 23 and August 15, 1968, in Test Cell J-4 of the Large Rocket Facility. This testing was in support of the J-2 engine application to the S-II and S-IVB stages of the Saturn V vehicle. The firings were accomplished at pressure altitudes between 78,000 and 110,000 ft at engine start. The primary objective of these firings was to evaluate engine start transients under various combinations of starting conditions with start tank energy being the major variable. The total accumulated firing duration for these four test periods w§&_223.2 sec

Thisy<Jocumi transmi only with prior a£$roval Huntsyille, Alabama

t Center (I-E-J),

This documenthss bc-n ~rr-r,„~AU u- i w,.., ---pp.oved rorpubfic re! its disiPbtfcn Is unlimited,fyufl

I

ease

\a. DD FORM ,1473 UNCLASSIFIED

Security Classification

UNCLASPIFIED Security Classification

KEY WORDS ROLE ROLE ROLE

J-2 rocket engines

liquid propellants

altitude simulation

flight simulation

startup

performance tests

performance evaluation

/.£r*^^ ^r^t*^-'

/V

'V

*V

UNCLASSIFIED Security Classification

UNCLASSIFIED AD NUMBER LIMITATION CHANGES62. Fuel Pump Start Transient Performance, Firing 06E . ....

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