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.
Qualified users may obtain copies of this report from the Defense Documentation Center.
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 sup- port 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
ils d'£::;-;bL!::c:T \z tfy.nited
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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
25. Thermal Conditioning History of Engine Components, Firing 04A 57
26. Engine Transient Operation, Firing 04A 58
27. Fuel Pump Start Transient Performance, Firing 04A . . 62
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
33. Thermal Conditioning History of Engine Components, Firing 04C 71
34. Engine Transient Operation, Firing 04C 72
35. Fuel Pump Start Transient Performance, Firing 04C . . 76
36. Engine Ambient and Combustion Chamber Pressure, Firing 04C 77
VI
AEDO-TR-68-238
Figure Page
37. Thermal Conditioning History of Engine Components, Firing 04D 78
38. Engine Transient Operation, Firing 04D 79
39. Fuel Pump Start Transient Performance, Firing 04D . . 81
4GL Engine Ambient and Combustion Chamber Pressure, .1.. Firing 04D 82
41. Thermal Conditioning History of Engine Components, Firing 05A 83
4-2. Engine Transient Operation, Firing 05A 84
43. Engine Ambient and Combustion Chamber Pressure, : . Firing 05A 86
44. Thermal Conditioning History of Engine Components, Firing 06A 87
45. Engine Transient Operation, Firing 06A 88
46. Fuel Pump Start Transient Performance, Firing 06A . . 92
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
52. Thermal Conditioning History of Engine Components, Firing 06C 101
53. Engine Transient Operation, Firing 06C 102
54. Fuel Pump Start Transient Performance, Firing 06C . . 106
55. Engine Ambient and Combustion Chamber Pressure, Firing 06C 107
56. Thermal Conditioning History of Engine Components, i Firing 06D 108
57. Engine Transient Operation, Firing 06D 109
58. Fuel Pump Start Transient Performance, Firing 06D . . 113
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 battle- ship 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, respec- tively.
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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 pro- duces, 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 in- jector 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 cham- ber 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 pneumat- ically 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.
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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 pre- valves, 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 pres- sure 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 sys- tems 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 cham- ber, 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) con- trol 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
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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 dif- fuser 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 pres- sure 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 cut- off, 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 tem- perature conditioning engine components. The conditioning system utilized a liquid hydrogen-helium heat exchanger to provide cold helium gas for component conditioning. Engine components requiring tempera- ture 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 dis- charge 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 param- eters 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 manu- facturer; 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 elec- trical 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 flow- meters; 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 re- corders, 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
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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 con- ducted within a 24-hr time period before an engine firing to verify the proper sequence of events. Facility and engine sequence checks con- sisted 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, gas- generator oxidizer injector, and thrust chamber jacket purges were initiated before evacuating the test cell. After com- pletion 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 accom- plished as required, using the facility-supplied engine component condi- tioning system. Engine components which required temperature condi- tioning 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.
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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 gener- ator outlet temperature first peak.
Results
Augmented spark igniter ig- nition 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 tem- perature first peak was 1640°F.
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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 out- let temperature transient with minimum start tank tempera- ture.
04C Simulate S -IVB first burn to evaluate augmented spark igniter ignition and gas gener- ator 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 gener- ator outlet temperature transient with maximum starting energy.
05A Simulate S-II firing to evaluate augmented spark igniter igni- tion with minimum augmented spark igniter mixture ratio, maximum fuel pump inlet pres- sure, and warmest thrust chamber.
Results
Thrust chamber ignition occurred at to + 0. 939 sec. Gas generator outlet tem- perature first peak was 2000°F with a second peak of 2190°F. Firing was terminated at to + 1.264 sec by engine safety cutoff sys- tem.
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 tem- perature 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 igni- tion 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 out- let temperature transient with minimum start tank tempera- ture.
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 tempera- ture 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 tem- perature 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 accom- plished. 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 accom- plished. 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 perform- ance 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 accom- plished. 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 perform- ance 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 oper- ating 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 pro- cedure) 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 accom- plished. 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 igni- tion was detected 0.180 sec after engine start. Thrust chamber igni- tion occurred at to + 0. 945 sec, and chamber pressure reached 550 psia at tQ + 2. 005 sec. Engine vibration in excess of 150 g oc- curred 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 accom- plished. 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 perform- ance 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 pres- sures. 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 accom- plished. 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 perform- ance 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 aug- mented 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 mini- mum 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 accom- plished. 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 perform- ance 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 tempera- ture 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 accom- plished. 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 perform- ance 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 igni- tion was detected 0.235 sec after engine start. Thrust chamber igni- tion 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 accom- plished. 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 perform- ance 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 accom- plished. 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 perform- ance 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 cham- ber 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 accom- plished. 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 perform- ance 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 com- mand. 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 mini- mum 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
Oxidizer Turbine Bypass Valve
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
Time Index Lines, 1-sec Intervals
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
Time Index Lines, 1-sec Intervals
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
c. Thrust Chamber Throat, TTC-1P
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
a. Thrust Chamber Fuel System, Start
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
b. Thrust Chamber Oxidizer System, Start
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
c. Thrust Chamber Fuel System, Shutdown
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
d. Thrust Chamber Oxidizer System, Shutdown
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
e. Gas Generator Injector Pressures and Main Oxidizer Valve Position, Start
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
f. Gas Generator Chamber Pressure and Temperature, Start
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
g. Gas Generator Injector Pressures, Shutdown
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
h. Gas Generator Chamber Pressure and Temperature, Shutdown
Fig. 14 Concluded
10
42
tn i O
CO
4 6
FLOW. QF-2. GPM X 10"3
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
c. Thrust Chamber Throat, TTC-1P
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
a. Thrust Chamber Fuel System, Start
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
b. Thrust Chamber Oxidizer System, Start
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
c. Thrust Chamber Fuel System, Shutdown
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
d. Thrust Chamber Oxidizer System, Shutdown
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
e. Gas Generator Injector Pressures and Main Oxidizer Valve Position, Start
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
f. Gas Generator Chamber Pressure and Temperature, Start
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
g. Gas Generator Injector Pressures, Shutdown
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
h. Gas Generator Chamber Pressure and Temperature, Shutdown
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
FLOW. QF-2. GPM X 10"3
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
a. Main Oxidizer Valve Second-Stage Actuator, TSOVC-1
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
b. Crossover Duct, TFTD 100
S -100 S
LU t—
-200
-300
[
CON )ITION NGTAR SET, 50 ±50°F- y
-2-1 -20 -16 -12 -8
TIME. HIN
c. Thrust Chamber Throat, TTC-1P
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
c. Thrust Chamber Throat, TTC-1P
Fig. 25 Thermal Conditioning History of Engine Components, Firing 04A
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
a. Thrust Chamber Fuel System, Start
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
b. Thrust Chamber Oxidizer System, Start
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
c. Thrust Chamber Fuel System, Shutdown
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
d. Thrust Chamber Oxidizer System, Shutdown
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
f. Gas Generator Chamber Pressure and Temperature, Start
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
g. Gas Generator Injector Pressures, Shutdown
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
FLOW, QF-2. GPM X 10"3
Fig. 27 Fuel Pump Start Transient Performance, Firing 04A
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
a. Main Oxidizer Valve Second-Stage Actuator, TSOVC-1
\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
b. Crossover Duct, TFTD
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
c. Thrust Chamber Throat, TTC-1P
Fig. 29 Thermal Conditioning History of Engine Components, Firing 04B
64
AEDC-TR.68-238
28 T 1400
&
Q. in
z: => Q-
1 2
TIME. SEC
a. Thrust Chamber Fuel System, Start
en
Ö
a. in a_ x:
TIME. SEC
b. Thrust Chamber Oxidizer System, Start
Fig. 30 Engine Transient Operation, Firing 04B
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
c. Thrust Chamber Fuel System, Shutdown
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
d. Thrust Chamber Oxidizer System, Shutdown
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
e. Gas Generator Injector Pressures and Main Oxidizer Valve Position, Start
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
f. Gas Generator Chamber Pressure and Temperature, Start
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
g. Gas Generator Injector Pressures, Shutdown
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
h. Gas Generator Chamber Pressure and Temperature, Shutdown
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
FLOW, QF-2. GPM X 10"3
Fig. 31 Fuel Pump Start Transient Performance, Firing 04B
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
a. Main Oxidizer Valve Second-Stage Actuator, TSOVC-1
e o
-100
-IB -12 -8
TIME. HIN
b. Crossover Duct, TFTD
100
2 -100 £
-200
-300
RGET. -. +20«. |co NDITI0NINGTA
Ns, ,
-
-2U -20 -IB -12 -8 -i| 0
TIME. HIN
c. Thrust Chamber Throat, TTC-1P
Fig. 33 Thermal Conditioning History of Engine Components, Firing 04C
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
a. Thrust Chamber Fuel System, Start
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
b. Thrust Chamber Oxidizer System, Start
Fig. 34 Engine Transient Operation, Firing 04C
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
c. Thrust Chamber Fuel System, Shutdown
35
tu a. in
I
TIME. SEC
d. Thrust Chamber Oxidizer System, Shutdown
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
e. Gas Generator Injector Pressures and Main Oxidizer Valve Position, Start
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
f. Gas Generator Chamber Pressure and Temperature, Start
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
g. Gas Generator Injector Pressures, Shutdown
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
Fig. 35 Fuel Pump Start Transient Performance, Firing 04C
-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
b. Crossover Duct, TFTD
8
I -100
-200
-300
'** /
/ cc NDITIO IINGT; RGET.i D±2fl \S
-2*4 -20 -8 -16 -12
TIME. HIN
c. Thrust Chamber Throat, TTC-1P
Fig. 37 Thermal Conditioning History of Engine Components, Firing 04D
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
a. Thrust Chamber Fuel System, Start and Shutdown
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
b. Thrust Chamber Oxidizer System, Start and Shutdown
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
Fig. 39 Fuel Pump Start Transient Performance, Firing 04D
> 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
Fig. 40 Engine Ambient and Combustion Chamber Pressure, Firing 04D
AEDCTR-68-238
100
Ö- 0
-100
-200
CONDITIONING TARGET, -100 ± 50°F —
• ■—
-HO -30 -10 -20
TIME, MIN
a. Main Oxidizer Valve Second-Stage Actuator, TSOVC-1
200
100
S:
-200
100
0X10IZER TURBINE -,
e^4 -.TFTD-8
CROSSOVER DUCT-' TFT">-3AN0 4
-20 -B -16 -12
TIME. MIN
b. Crossover Duct, TFTD
-U
2 -100
1 UJ
-200
-300
\ CONDITION IMG TARGET, -1 ■» N, '
...
-at -20 -16 -12 -8 -1 0
TIME, MIN
c. Thrust Chamber Throat, TTC-1P
Fig. 41 Thermal Conditioning History of Engine Components, Firing 05A
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
a. Thrust Chamber Fuel System, Start and Shutdown
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
b. Thrust Chamber Oxidizer System, Start and Shutdown
Fig. 42 Engine Transient Operation, Firing 05A
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. Main Oxidizer Valve Second-Stage Actuator, TSOVC-1
a-
s s
-200
100
TIME. MIN
b. Crossover Duct, TFTD
-100
-200
-300
\ \
\ -
CONDITIONING TARGET. -200 ± Z 5°F-,
■
-24 -20 -4 -IB -12 -8
TIME. HIN
c. Thrust Chamber Throat, TTC-1P
Fig. 44 Thermal Conditioning History of Engine Components, Firing 06A
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
a. Thrust Chamber Fuel System, Start
10T 1000
S: o UJ
TIME. SEC
b. Thrust Chamber Oxidizer System, Start
Fig. 45 Engine Transient Operation, Firing 06A
88
AEDC-TR-68-238
0. oc
in a.
Q_
TIME. SEC
c. Thrust Chamber Fuel System, Shutdown
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
f. Gas Generator Chamber Pressure and Temperature, Start
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
g. Gas Generator Injector Pressures, Shutdown
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
h. Gas Generator Chamber Pressure and Temperature, Shutdown
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
FLOW, QF-2. GPM X 10"3
8 10
Fig. 46 Fuel Pump Start Transient Performance, Firing 06A
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
a. Main Oxidizer Valve Second-Stage Actuator, TSOVC-1
800
600
400
300
-16 -12
TIME, MIN
b. Crossover Duct, TFTD
100
% -100
-200
-300
_ ;
ITIONto T, 50* TARG Z5°F^
/
1
-2« -20 -16 -12
TIME. MIN
-II
c. Thrust Chamber Throat, TTC-1P
Fig. 48 Thermal Conditioning History of Engine Components, Firing 06B
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
a. Thrust Chamber Fuel System, Start
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
b. Thrust Chamber Oxidizer System, Start
Fig. 49 Engine Transient Operation, Firing 06B
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
c. Thrust Chamber Fuel System, Shutdown
10
a. cc
UJ a. in
10T IOOO
8-
6-- to Q_
4 ■
2-
O1
cc in UJ cc
TIME. SEC
d. Thrust Chamber Oxidizer System, Shutdown
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
e. Gas Generator Injector Pressures and Main Oxidizer Valve Position, Start
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
f. Gas Generator Chamber Pressure and Temperature, Start
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
h. Gas Generator Chamber Pressure and Temperature, Shutdown
Fig. 49 Concluded
98
m i O
CO
d LÜ
4 6
FLON, QF-2. GPM X 10"3
Fig. 50 Fuel Pump Start Transient Performance, Firing 06B
> 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
a. Main Oxidizer Valve Second-Stage Actuator, TSOVC-1
S
-16 -12 -8
TIME. HIN
b. Crossover Duct, TFTD 100
5 -100
-200
-300
\_
\ \
ICONDIT .TARGET
I0NING -250±25°r-^
\
) ■
-21 -20 -16 -12 -8 -1 0
TIME. HIN
c. Thrust Chamber Throat, TTC-1P
Fig. 52 Thermal Conditioning History of Engine Components, Firing 06C
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
b. Thrust Chamber Oxidizer System, Start
Fig. 53 Engine Transient Operation, Firing 06C
.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
d. Thrust Chamber Oxidizer System, Shutdown
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
f. Gas Generator Chamber Pressure and Temperature, Start
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
g. Gas Generator Injector Pressures, Shutdown
£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
h. Gas Generator Chamber Pressure and Temperature, Shutdown
Fig. 53 Concluded
35
105
ro i O
o
cr
> m o n ■
70 i.
4 6
FLOW. QF-2. GPM X 1CT3
Fig. 54 Fuel Pump Start Transient Performance, Firing 06C
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
b. Crossover Duct, TFTD 100
? -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
c. Thrust Chamber Throat, TTC-1P
Fig. 56 Thermal Conditioning History of Engine Components, Firing 06D
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. Thrust Chamber Fuel System, Start
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
b. Thrust Chamber Oxidizer System, Start
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
d. Thrust Chamber Oxidizer System, Shutdown
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
e. Gas Generator Injector Pressures and Main Oxidizer Valve Position, Start
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
f. Gas Generator Chamber Pressure and Temperature, Start
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
Fig. 58 Fuel Pump Start Transient Performance, Firing 06D
> 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
Fig. 59 Engine Ambient and Combustion Chamber Pressure, Firing 06D
AEDC-TR-68-238
100
i— er EC
-100
-200
CONDITIONING TARGET, -UOlSlfr^
- s»
,.
-40 -30 -10 -20
TIME. MIN
a. Main Oxidizer Valve Second-Stage Actuator, TSOVC-1
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
b. Crossover Duct, TFTD
100
2 -loo E
-200
-300
cot ID IT ION INGTA IGET, - tx>±& *"\ V
\
JN
-2>1 -20 -8 -IS -12
TIME. MIN
c. Thrust Chamber Throat, TTC-1P
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
a. Thrust Chamber Fuel System, Start and Shutdown
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
b. Thrust Chamber Oxidizer System, Start and Shutdown
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 Turbine Bypass Valve
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
Start Tank Conditions at Engine Start
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
Crossover Duct Temperature
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
Start Tank Conditions at Engine Start
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 -—-"*
Crossover Duct Temperature
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
Oxidizer Turbine Bypass Valve
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 Delay Time, sec
Valve Opening
Time, sec
Time of
Opening Signal
Valve Delay Time, sec
Valve Opening Time, sec
Time of
Opening Signal
Valve Delay Time, sec
Valve Time Opening' of Time, Closing sec Signal
Valve Delay Time, sec
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 Delay Time, sec
Valve Closing Time,
sec
Time of
Closing Signal
Valve Delay Time, sec
Valve Closing Time,
sec
Time of
Closing Signal
Valve Delay Time, sec
Valve Closing Time, sec
Time of
Closing Signal
Valve Delay Time, sec
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
TSC2-20 Thrust Chamber Skin -300 to +600 X
TSC2-24 Thrust Chamber Skin -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
UTCD-2 Thrust Chamber Dome
UTCD-3 Thrust Chamber Dome
UTCD-4 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 normal- ized 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