The requirement of the Space Shuttle rocket engine for liquid hydrogen pump pressure rise equivalent to 200.000 feet (65610 m) of head, along with a wide range, necessitated the use of a multistage centrifugal pump. These pumps require the use of diffusing crossover passages extending from the discharge of one impeller to the inlet of the following impeller. The work discussed includes the design and air test of three prototype diffusing crossovers and the design and water test of the production type Space Shuttle Main Engine (SSME) high-pressure hydrogen pump crossover. The prototype crossovers were tested in an air rig with the flow provided by an existing 24-blade impeller. Static pressures were measured throughout the passages, and a total pressure profile was obtained at the exit. The air test hardware included an axial vaned diffuser, multiple vaned passages, and a continuous passage design. A continuous passage design was selected as the production version to minimize fabrication and structural problems. The production continuous passage type crossover was tested in the Rocketdyne pump test facility with the crossover flow driven by the production type hydrogen pump impeller. Water was used as the test fluid. Static pressures were measured throughout the flow passages, and total pressures were measured at the crossover passsage exit.
Experimental evaluation of diffusing crossover systems for a high-pressure liquid hydrogen pump
Experimentelle Entwicklung von Diffusionsuebergangssystemen fuer eine Hochdruckfluessigwasserstoffpumpe
1983
8 Seiten, 23 Bilder, 4 Tabellen, 8 Quellen
Aufsatz (Konferenz)
Englisch
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