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

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

  • 330 Want to read
  • ·
  • 45 Currently reading

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

Subjects:

  • 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
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL14662976M

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

PDF EPUB FB2 MOBI RTF

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.