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LH2 pump component development testing in the electric pump room at test cell C inducer no. 1The characteristics of a turbine pump for use with the nuclear engine for rocket vehicles are discussed. It was determined that the pump will be a two stage centrifugal pump with both stages having backswept impellers and an inducer upstream of the first stage impeller. The test program provided demonstration of the ability of the selected design to meet the imposed requirements.
Document ID
19730015803
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Andrews, F. X.
(Aerojet-General Corp. Sacramento, CA, United States)
Brunner, J. J.
(Aerojet-General Corp. Sacramento, CA, United States)
Kirk, K. G.
(Aerojet-General Corp. Sacramento, CA, United States)
Mathews, J. P.
(Aerojet-General Corp. Sacramento, CA, United States)
Nishioka, T.
(Aerojet-General Corp. Sacramento, CA, United States)
Date Acquired
September 2, 2013
Publication Date
May 1, 1972
Subject Category
Machine Elements And Processes
Report/Patent Number
NASA-CR-132232
N8300R:72-101
Accession Number
73N24530
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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