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Small, high-pressure, liquid oxygen turbopumpA small, high-pressure, LOX turbopump was designed, fabricated, and tested. The pump was of a single-stage, centrifugal type; power to the pump was supplied by a single-stage, partial-admission, axial-impulse turbine. Design conditions included an operating speed of 7330 rad/sec (70,000 rpm) pump discharge pressure of 2977 N/sq cm (4318 psia), and a pump flowrate of 16.4 kg/s (36.21 lb/sec). The turbine was propelled by LOX/LH2 combustion products at 1041 K (1874 R) inlet temperature, and at a design pressure ratio of 1.424. Test data obtained with the turbopump are presented and mechanical performance is discussed.
Document ID
19790009050
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Csomor, A. (Rockwell International Corp. Canoga Park, CA, United States)
Date Acquired
September 3, 2013
Publication Date
October 1, 1978
Subject Category
Mechanical Engineering
Report/Patent Number
RI/RD78-278
NASA-CR-159509
Accession Number
79N17221
Funding Number(s)
CONTRACT_GRANT: NAS3-17800
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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