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Orbital transfer vehicle oxygen turbopump technology. Volume 3: Hot oxygen testingThis report covers the work done in preparation for a liquid oxygen rocket engine turbopump test utilizing high pressure hot oxygen gas for the turbine drive. The turbopump (TPA) is designed to operate with 400 F oxygen turbine drive gas. The goal of this test program was to demonstrate the successful operation of the TPA under simulated engine conditions including the hot oxygen turbine drive. This testing follows a highly successful series of tests pumping liquid oxygen with gaseous nitrogen as the turbine drive gas. That testing included starting of the TPA with no assist to the hydrostatic bearing. The bearing start entailed a rubbing start until the pump generated enough pressure to support the bearing. The articulating, self-centering hydrostatic bearing exhibited no bearing load or stability problems. The TPA was refurbished for the hot gas drive tests and facility work was begun, but unfortunately funding cuts prohibited the actual testing.
Document ID
19930021850
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Urke, Robert L. (Aerojet-General Corp. Sacramento, CA, United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1992
Subject Category
Mechanical Engineering
Report/Patent Number
NASA-CR-191036
NAS 1.26:191036
AD-A265708
Accession Number
93N31039
Funding Number(s)
CONTRACT_GRANT: NAS3-23772
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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