Space Shuttle Main Engine Orientation
BC98-04Space Transportation SystemTraining DataSpace ShuttleMain EngineOrientationJune 1998Use this data for training purposes onlyRocketdynePropulsion & Power
BOEING PROPRIETARYFORWARDThis manual is the supporting handout material to a lecture presentation on the Space ShuttleMain Engine called the Abbreviated SSME Orientation Course. This course is a technicallyoriented discussion of the SSME, designed for personnel at any level who support SSME activitiesdirectly or indirectly. This manual is updated and improved as necessary by Betty McLaughlin.To request copies, or obtain information on classes, call Lori Circle at Rocketdyne (818) 586-2213BOEINGBOEING PROPRIETARYPROPRIETARYi1684-1a.ppt
BOEING PROPRIETARYTABLE OF CONTENTAcronyms and Abbreviations. vLow-Pressure Fuel Turbopump. 56Shuttle Propulsion System.2HPOTP Pump Section. 60SSME Introduction. 4HPOTP Turbine Section. 62SSME Highlights. 6HPOTP Shaft Seals. 64Gimbal Bearing. 10HPFTP Pump Section. 68Flexible Joints. 14HPFTP Turbine Section. 70Powerhead. 16POGO Accumulator Pressurizing System . 72Propellant Flow Analysis. 18POGO Suppression System Accumulator. 74Powerhead. 22ASI Injector/Combustion Chamber.76Hot Gas Manifold. 24ASI Spark Igniter. 78Fuel Preburner. 28Control System Interface. 80Oxidizer Preburner. 32Pneumatic Control Assembly. 82Heat Exchanger. 36Propellant Valve Hydraulic Actuator. 84Main Injector.40Hydraulic Servovalve Operation. 86Main Combustion Chamber.44Hydraulic Actuator Piston Configuration. 88Nozzle . 48Controller. 90Low-Pressure Oxidizer Turbopump.52Controller Functional Organization. 92BOEINGBOEING PROPRIETARYPROPRIETARYii1684-1a.ppt
BOEING PROPRIETARYLIST OF ILLUSTRATIONSSpace Shuttle Launch. 1Space Shuttle Overview. 3Space Shuttle Main Engine Overview. 5SSME Typical Throttling Profile. 7Orbiter Main Propulsion System . 8SSME Component Location. 9Gimbal Bearing. 11Typical Flex Bellows Applications. 12Internally Tied Flex Joints.13Flex Joints with Insulating Jacket. 15Powerhead Component Arrangement. 17Propellant Flow Schematic. 19Powerhead. 23Hot Gas Manifold. 25Hot Gas Manifold/Injector Assembly. 26Typical SSME View 1. 27Fuel Preburner. 29Fuel Preburner Nomenclature. 30Typical SSME View 2. 31Oxidizer Preburner. 33Oxidizer Preburner Nomenclature. 34Typical SSME View 3. 35Heat Exchanger Assembly. 37Heat Exchanger Nomenclature. 38Typical SSME View 4. 39Main Injector.41Main Injector Nomenclature. 42Typical SSME View 5. 43Main Combustion Chamber .45MCC Nomenclature.46Main Combustion Chamber Photo. 47Nozzle. 49Nozzle Nomenclature. 51Low-Pressure Oxidizer Turbopump. 53LPOTP Nomenclature. 54Typical SSME View 6. 55Low-Pressure Fuel Turbopump. 57LPFTP Nomenclature. 58High-Pressure Oxidizer Turbopump. 59HPOTP Pump Section. 61HPOTP Turbine Section. 63HPOTP Seal Group. 65High-Pressure Fuel Turbopump. 67HPFTP Pump Section. 69HPFTP Turbine Section. 71POGO Suppression System Schematic. 73POGO Suppression Accumulator. 75Preburner Augmented Spark Igniter. 77Spark Igniter. 79SSME Control Systems Interfaces. 81Pneumatic Control Assembly. 83Propellant Valve Hydraulic Actuator. 85BOEINGBOEING PROPRIETARYPROPRIETARYiii1684-1a.ppt
BOEING PROPRIETARYLIST OF ILLUSTRATIONSServovalve Assembly. 87Preburner Valve Actuator . 89Controller.91Controller Organization. 93Engine Valve Sequence at Start. 94Engine Valve Sequence at Shutdown. 95Typical SSME View 7. 96Typical SSME View 8. 97SSME Complete Fluid Schematic. 99BOEINGBOEING PROPRIETARYPROPRIETARYiv1684-1a.ppt
BOEING PROPRIETARYACRONYMS AND SCOSFBVFPBFPLFPOVFPOVAFRIGCVGGGN O 2LOXLPFLPFTPLPOLPOTPAnti-Flood ValveAugmented Spark IgniterChamber Coolant ValveChamber Coolant Valve ActuatorCorrosion Resistant SteelDirect CurrentDigital Computer UnitElectrodeposited CopperElectrodeposited NickelEngine Interface UnitExternal TankFlight Acceleration Safety Cutoff SystemFuel Bleed ValveFuel PreburnerFull Power LevelFuel Preburner Oxidizer ValveFuel Preburner Oxidizer Valve ActuatorFlow Recirculation InhibitorGOX Control ValveGas GeneratorGaseous NitrogenGaseous OxygenGeneral Purpose ComputerGround Support EquipmentHydrogenHeat ExchangerHydrogen Embrittlement EnvironmentHot Gas ManifoldHigh-Pressure FuelHigh-Pressure Fuel TurbopumpHigh-Pressure OxidizerHigh-Pressure Oxidizer TurbopumpHelium Precharge ValveInput ElectronicsLeft HandLiquid HydrogenLiquid OxygenLiquid OxygenLow-Pressure FuelLow-Pressure Fuel TurbopumpLow-Pressure OxidizerLow-Pressure Oxidizer RIVRPLRPMRVDTSPGGSRBSSMETEBBTERBVDCWDTZRO 2PROPRIETARYBOEINGBOEING PROPRIETARYvLine Replaceable UnitLarge Throat Main Combustion ChamberLinear Variable Differential TransformerMaximumMain Combustion ChamberMain Engine ControllerMain Fuel ValveMain Fuel Valve ActuatorMain InjectorMain Oxidizer ValveMain Oxidizer Valve ActuatorMinimum Power LevelMixture RatioNormally ClosedNormally OpenedNormal Power LevelOxidizer Bleed ValveOutput ElectronicsOrbital Maneuvering SystemOxidizer PreburnerOxidizer Preburner Oxidizer ValveOxidizer Preburner Oxidizer Valve ActuatorOrbiter VehiclePressure Actuated ValvePump End Ball BearingPreburnerPneumatic Control AssemblyPounds Per Square InchReaction Control SystemRight HandRecirculation Isolation ValveRated Power LevelRevolutions Per MinuteRotary Variable Differential TransformerSolid Propellant Gas GeneratorSolid Rocket BoosterSpace Shuttle Main EngineTurbine End Ball BearingTurbine End Roller BearingVolts direct CurrentWatchdog TimerZirconium Oxide1684-1a.ppt
Space Shuttle Launch at Kennedy Space CenterRocketdynePropulsion & PowerBOEING PROPRIETARY19804019c.pptsa/rl
SHUTTLEPROPULSIONSYSTEMBOEINGPROPRIETARYThe Space Shuttle propulsion system consists of two large solid rocket booster (SRB) motors, three space shuttle main engines (SSME),and an external propellant tank (ET), all used to boost the shuttle orbiter into space. In addition, the orbiter contains two orbitalmaneuvering system (OMS) engines, and 44 reaction control system (RCS) thrusters.Each SRB measures 12 feet in diameter by 149 feet in height, weighs 1.3 million pounds, and generates approximately 3.3 million poundsof thrust. The SRBs also serve as launch pad mounts for the entire vehicle and are ignited at launch after all three SSMEs are producingat least 90-percent thrust. The solid propellant consists of a cast mixture of ammonium perchlorate (oxidizer, 69.93 percent by weight),atomized aluminum powder (fuel, 16.00 percent), polymer (binder, 12.04 percent), epoxy (curing agent, 1.96 percent), and iron oxide(catalyst, 0.07 percent). After burnout at approximately 150,000 feet, the spent cases separate from the vehicle, arcing up toapproximately 220,000 feet before parachuting to the ocean for recovery and reuse.The External Tank, at 154 feet long by 27.5 feet in diameter is the largest element of the Space Shuttle. It serves as the backbonestructure for attachment of the Orbiter and SRBs and also contains and delivers propellants under pressure to the three Orbiter mainengines. The ET must accommodate the stresses created by its own weight, when loaded with propellants, and that of the Orbiter priorto launch. Then at launch the thrust generated by the Orbiter and the SRBs must be reacted by the ET structure. The ET has three majorcomponents: The forward liquid oxygen tank, the aft liquid hydrogen tank, and an unpressurized intertank that joins the two propellanttanks. After the SSMEs are shut down, the ET is jettisoned, enters the Earth’s atmosphere, breaks up, and the pieces that survive reentryimpact in a remote ocean area. It is the only element of the Space Shuttle that is not recovered.The three SSMEs, which are sequentially started at launch, combust a mixture of propellants consisting of hydrogen and oxygen, whichare stored and delivered in a cryogenic liquid state from the external tank (ET). Throttling-down of engine thrust is necessary early in theascent to prevent excessive aerodynamic loading of vehicle structure and later in the flight to limit vehicle acceleration to no more than 3times normal Earth gravity. Each engine is gimballed through two planes for vehicle pitch, yaw, and roll control. The SSMEs steer andaccelerate the vehicle to the desired orbital position and velocity, and shut down.The two OMS engines are mounted in pods on either side of the orbiter vertical stabilizer. Each pod also contains engine propellanttanks and helium tanks used for propellant tank pressurization. The propellants used are monomethylhydrazine (fuel) and nitrogentetroxide (oxidizer), which are hypergolic (ignite on contact). Each engine produces 6,000 pounds of thrust in a vacuum. They are usedtogether or separately to increase or decrease orbiter velocity for orbit insertion, circularization, transfer, and deorbit. The OMS pods,which are detachable, are serviced in a dedicated facility and reattached to the orbiter during ground turnaround activities. The podsalso contain the aft group of reaction control system thrusters.The reaction control system provides the capability for rotation and translation maneuvers of an orbiter in space. It includes 38 primarythrusters (870 pounds thrust each), and six vernier thrusters (24 pounds thrust each). The forward thruster group (in the orbiter nose)includes 14 primary and two vernier thrusters. Each OMS pod contains 12 primary and two vernier thrusters. Each thruster can fire apulse as short as 800 milliseconds, using monomethylhydrazine (fuel) and nitrogen tetroxide (oxidizer), which are hypergolic. TypicalRCS uses are: Attitude control as required, roll control during a one-OMS engine burn, orbiting and deorbiting (if the OMS fails),rendezvous and docking, and station keeping.BOEINGBOEING PROPRIETARYPROPRIETARY21684-1a.ppt
Space ShuttleOrbiter - 1,805 nmiCross RangeExternalPropellantTankCrew ModuleCommanderPilotMission SpecialistPayload SpecialistUp to 6 PassengersPayload CapabilityDiameter 15 ftLength 60 ftWeight 55,000 lbDue East Launch2 Orbital ManeuveringSystem EnginesThrust 6,000 lb EachTwo 146-in. Diameter Solid Rocket BoostersThrust 3.3M lb EachRocketdynePropulsion & Power3 Space Shuttle Main EnginesThrust 470,800 lb Each39804015c.pptaw/rl
BOEINGPROPRIETARYSSMEINTRODUCTIONThe Space Shuttle Main Engine is a staged combustion cycle engine that burns a mixture of gaseoushydrogen and liquid oxygen. The identifying feature of a staged combustion engine is that most of thefuel flow (except for a small coolant flow) and a small amount of the oxidizer flow are “preburned” in apreburner at an extremely fuel-rich mixture. The resulting fuel-rich hot gas is used to power theturbopump turbine, and then injected into the main combustion chamber (MCC) along with the remainingoxidizer and the coolant fuel, all to be “final-burned”.The SSME is rated at 470,800 pounds thrust (100 percent) in vacuum of 376,600 pounds at sea level. It isthrottleable from 316,100 pounds (67 percent) to 512,900 pounds (109 percent) in approximately 4,700pound (1-percent) increments. These three thrust levels are called rated power level (RPL), minimumpower level (MPL), and full power level (FPL), respectively. Throttling is accomplished by varying theoutput of the preburners, thus varying the speed of the high-pressure turbopumps and, therefore, thepropellant mass flowrates. The pressure of the burning propellants within the MCC is approximately3,008 pounds per square inch (PSI) at FPL. The MCC propellant mixture ratio is approximately 6 poundsof oxygen to 1 pound of hydrogen, maintained by varying the fuel flowrate around the oxidizer flowrate.A large nozzle with a fairly high expansion ratio of 69 to 1 (nozzle exit area versus throat area) is requiredto fully expand the very high pressure gas in the MCC. Specific impulse in vacuum is 452 seconds (i.e.,452 pounds of thrust is generated for each pound of propellant burned per second).In order to start, the SSME needs only propellant head for initial propellant flow and spark igniters toinitiate combustion. It has an electronic controller to perform all checkout, start, run, monitoring, andshutdown functions. The engine is gimballed through two planes by hydraulic actuators for vehiclepitch, yaw, and roll control.BOEINGBOEING PROPRIETARYPROPRIETARY41684-1a.ppt
SSME Is the First Reusable LargeLiquid Rocket Engine14 ft en RatedRated powerpower levellevel (RPL)(RPL)100%100% NominalNominal powerpower levellevel(NPL)(NPL) 104.5%104.5% FullFull powerpower levellevel (FPL)(FPL)109%109% ChamberChamber pressurepressure(109%)(109%) SpecificSpecific impulseimpulse atataltitudealtitude ThrottleThrottle rangerange (%)(%) WeightWeight TotalTotal programprogram hot-firehot-firetimetime470,800470,800 lblb491,900491,900 lblb512,900512,900 lblb3,0083,008 psiapsia452452 secsec6767 toto 1091097,4807,480 lblb 2,6602,660 startsstarts 832,500832,500 secsec7.5 ftRocketdynePropulsion & PowerBOEING PROPRIETARY59804012c.pptaw/rl
SSMEHIGHLIGHTSBOEINGPROPRIETARY Power cycle: Staged combustion. Fuel-rich combustion gas from two preburners drives two highpressure turbopumps and then injects with oxidizer into main combustion chamber. High-energy propellants: Liquid oxygen/liquid hydrogen Delivered by two high-pressure and two low-pressure (boost) turbopumps Main combustion propellant mixture ratio is 6.032 lbs oxygen to 1 lb hydrogen Variable thrust: Full Power Level (FPL) . 109% Nominal Power Level (NPL).104.5% Rated Power Level (RPL).100% Minimum Power Level (MPL).67% Variable in 1% increments.1%(512,900 lbs)(491,900 lbs)(470,800 lbs)(316,100 lbs)( 4,700 lbs) High efficiency: Specific impulse approximately 452 seconds Two-stage combustion approximately 99.6% efficient Main chamber pressure approximately 3,008 psi at FPL Direct drive turbopumps (no reduction gears) High expansion ratio (69 to 1) (nozzle exit area vs. throat area) Simple start system: Tank head pressure starts propellant flow Spark igniters initiate combustion No start tanks, turbine spinners, pyrotechnics, pressure ladders, etc. On-board controller: Checkout, start, run, throttling, mixture ratio, monitoring, shutdown, etc. Hydraulically-driven propellant valves (pneumatic backup for closing) Pogo suppression system (pressurized accumulator in LOX feed system) Gaseous Hydrogen and Oxygen tank repressurization systemBOEINGBOEING PROPRIETARYPROPRIETARY61684-1a.ppt
SSME Typical Throttling Profile105100953-G limit throttle90PowerLevel85in Percentof RPL80Max-Q throttle down to protectagainst excessive aerodynamicloading on the 0550Time in SecondsRocketdynePropulsion & PowerBOEING PROPRIETARY79804082.pptbg/rl
Main Propulsion SystemRocketdynePropulsion & PowerBOEING PROPRIETARY89804020c.pptsa/rl
BOEING PROPRIETARYSSME Component LocationLooking AftGimbal BearingOxidizer PreburnerOxidizer ValveLow-PressureFuel TurbopumpOxidizer PreburnerFuel Tank PressurantNitrogen SupplyFuel Bleed ValveMain Fuel ValveHelium SupplyHydraulic ReturnHydraulic SupplyOxidizer TankPressurantFuel PreburnerOxidizer BleedValveFuel BleedOxidizer BleedLow-PressureOxidizer PumpFuel PreburnerOxidizer ValveElectrical InterfacePanelRocketdynePropulsion & PowerBOEING PROPRIETARY99804070.pptbg/ls
BOEINGGIMBALPROPRIETARYBEARINGThe gimbal bearing provides a means of attaching the engine to the vehicle while allowing the engine tobe pivoted (gimballed) around its two axes. This is necessary in order to point the engine thrust vectorfor vehicle steering, in the manner of a ship’s rudder.The gimbal bearing is bolted to the vehicle by its upper flange and to the engine by its lower flange. Itsupports 7,480 pounds of engine weight and withstands over 500,000 pounds of thrust. It is a ball-andsocket universal joint in which concave and convex spherical surfaces on the seat, body, and blockintermesh. Sliding contact occurs between these surfaces as the bearing is angulated. Fabroid insertslocated at the sliding contact surfaces reduce friction that occurs during gimbal bearing angulation.
This manual is the supporting handout material to a lecture presentation on the Space Shuttle Main Engine called the Abbreviated SSME Orientation Course. This course is a technically oriented discussion of the SSME, designed for personnel at any
1.Engine Oil SABA 13 1.Engine Oil 8000 14 1.Engine Oil 6000 15 1.Engine Oil 3000 16 1.Engine Oil Alvand 17 1.Engine Oil Motor Cycle Engine Oil M-150 18 1.Engine Oil M-100 19 1.Engine Oil Gas Engine Oil CNG-BUS 20 1.Engine Oil G.I.C.X.LA 21 1.Engine Oil G.I.C.X. 22 1.Engine Oil Diesel Engine Oil Power 23 1.Engine Oil Top Engine 24
on model) under the brew head. Turn on the warmer if a shuttle is used. 3) If the shuttle is not warm, allow the warmer to heat the shuttle. Only a short brew of water will speed this. A cold shuttle will significantly lower the temperature of the brewed coffee. 4) Remove the filter basket and line with a filter paper. Paper size is 13 x 5 for .
Framework for a Space Shuttle Main Engine Health Monitoring System (NASA-CR-I852_) FRAMEWORK FOR A &PACE SHUTTLE MAIN _NGINL _FALTH _(]NITORING SYSTEM Final Report (United Technologies Research Center) 189 p CSCL 21H Michael W. Hawman, William S. Galinaitis, Sharayu Tulpule, and Anita K. Mattedi United Technologies Research Center East Hartford .
Space Shuttle Missions: Advancing Earth Observations and Mapping Shuttle and Imaging Radars—A Quiet Revolution in Earth Mapping The First Mission The Shuttle Imaging Radar-A flew on Space Shuttle Columbia (Space Transportation System [STS]-2) in November1981. This radar was compr
Space Shuttle Body Flap Actuator Bearing Testing for NASA Return to Flight Timothy R Jett', Roamer E. Predmore'*, Michael J. Dube" and William R. Jones, Jr ) Abstract The Space Shuttle body flap (BF) is located beneath the main engine nozzles and is required for proper aerodynamic control during orbital descent.
2022 FALL Semester Weekday Schedule Looping Shuttle Service PEAK SERVICE HOURS PEAK SERVICES BETWEEN - 7:30 a.m. TO 10:52 a.m. PEAK SERVICES BETWEEN - 3:00 p.m. TO 6:02 p.m. August 22 - 25th First year Orientation Monday - Thursday Shuttle Services 7:45 a.m. - 6:00 p.m. Saturday, August 27th Regular Schedule - ALL Classes in Session Monday's classes end at 8:30 p.m. Shuttle Services .
The Block II Space Shuttle Main Engine includes a new high-pressure fuel turbopump developed by Pratt & Whitney of West Palm Beach, Fla. The new design eliminates welds by using a . Stennis tests aerospike engine technology, page 3 SLI holds first technical workshop, page 4 Space Transportation Day on the Hill, page 6
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