Space shuttle main engine high pressure fuel pump aft platform seal cavity flow analysis
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Space shuttle main engine high pressure fuel pump aft platform seal cavity flow analysis

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Published by National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in [Washington, D.C.], [Springfield, Va .
Written in English


  • Fluid mechanics.,
  • Rocket engines -- Fuel systems.,
  • Fuel pumps.

Book details:

Edition Notes

StatementS.A. Lowry, L.W. Keeton.
SeriesNASA technical paper -- 2685.
ContributionsKeeton, L. W., United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
The Physical Object
Pagination1 v.
ID Numbers
Open LibraryOL14662976M

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Space shuttle main engine high pressure fuel pump aft platform seal cavity flow analysis / By S. A. Lowry, L. W. Keeton and George C. Marshall Space Flight Center. Abstract. Prepared at George C. Marshall Space Flight Center."January "es bibliographical references (p. 51).Mode of access: Internet. A general purpose, three-dimensional computational fluid dynamics code named PHOENICS, developed by CHAM Inc., is used to model the flow in the aft-platform seal cavity in the high pressure fuel pump of the space shuttle main engine. Space Shuttle Main Engine Turbopump Developed in the s by Marshall Space Flight Center in Huntsville, Ala., the Space Shuttle Main fuel flow and reduced the pressure and temperature allows the high-pressure pumps to operate at lower turbine temperatures and pressures. space shuttle main engine low-pressure fuel duct controller low-pressure fuel turbopump low-pressure oxidizer tur- high pressure fuel duct fuel preburner main fuel valve fuel preburner oxidizer valve oxidizer pre-burner hot-gas (from inside aft section looking out) ssme no. .

  Space Shuttle Main Engine High Pressure Fuel Pump Aft Platform Seal Cavity Flow Analysis,” NASA Marshall Space Flight Center, Huntsville, AL, Technical Paper No. NASA-TP It remains low at 4 to 5 bars, i.e. the pressure generated by the fuel pump in your fuel tank (picture to the right). It could fluctuate up to 7 bars and drop back to 4 or 5. The HPFP did not obey the instruction which denotes a failure. ON HOT ENGINE-Plug your scanner and go straight away to the measured common rail pressure. Full text of "STS Space Shuttle mission report" See other formats r> NASA-GR V «;. NSTS STS SPACE SHUTTLE MISSION REPORT NASA-CRO U (NASA-CR) STS SPACE SHUTTLE MISSION REPORT (Lockheed Engineering and Sciences Co.) 32 p N Unci as * G3/16 ' February r- LIBRARY COPY. Transitioning from working on the old-school conventional (mechanical) diesel fuel injection systems to the modern, computerized High-Pressure Common-Rail (HPCR) fuel system requires a change in thinking and a change in diagnostic procedures. We’ve all heard the phrase ‘you can’t teach an old dog new tricks’ but we’re going to smarten you up by offering you our 5 tips to ensure the.

There are number of components can be found in aircraft turbine engine fuel system. Engine driven fuel pumps categories are constant and nonconstant displacement. Gear-type pumps have approximately straight line flow characteristics, when the fuel cools to 32 °F or below residual water in the fuel tends to freeze, forming ice crystals. Methods of regulating fuel temperature; three common. A lot of technology in the high pressure pumps, both fuel and oxidizer. The main problem with the high pressure fuel pump was sub-synchronous whirl, and I'll say a little bit more about this in a moment. It was a very traumatic time in the early period of developing the Shuttle main engine. It caused a lot of delays. A tough problem to solve. The nozzles of Space Shuttle Columbia's three RSs following the landing of STS The engine's nozzle is in (Template:Convert/round m) long with a diameter of in (Template:Convert/round m) at its throat and in (Template:Convert/round m) at its exit. The nozzle is a bell-shaped extension bolted to the main combustion chamber, referred to as a de Laval nozzle. On J at T+, both temperature sensors for the Space Shuttle Main Engine (SSME) 1 high pressure fuel turbopump showed readings exceeding the redline limit. This resulted in a premature shutdown of SSME 1 and declaration of an Abort to Orbit condition, the first in program history.