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Rocketdyne LOX bearing tester programThe cause, or causes, for the Space Shuttle Main Engine ball wear were unknown, however, several mechanisms were suspected. Two testers were designed and built for operation in liquid oxygen to empirically gain insight into the problems and iterate solutions in a timely and cost efficient manner independent of engine testing. Schedules and test plans were developed that defined a test matrix consisting of parametric variations of loading, cooling or vapor margin, cage lubrication, material, and geometry studies. Initial test results indicated that the low pressure pump thrust bearing surface distress is a function of high axial load. Initial high pressure turbopump bearing tests produced the wear phenomenon observed in the turbopump and identified an inadequate vapor margin problem and a coolant flowrate sensitivity issue. These tests provided calibration data of analytical model predictions to give high confidence in the positive impact of future turbopump design modification for flight. Various modifications will be evaluated in these testers, since similar turbopump conditions can be produced and the benefit of the modification will be quantified in measured wear life comparisons.
Document ID
19900019310
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Keba, J. E. (Rockwell International Corp. Canoga Park, CA, United States)
Beatty, R. F. (Rockwell International Corp. Canoga Park, CA, United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1988
Publication Information
Publication: NASA, Marshall Space Flight Center, Advanced Earth-to-Orbit Propulsion Technology 1988, Volume 1
Subject Category
Mechanical Engineering
Accession Number
90N28626
Funding Number(s)
CONTRACT_GRANT: NAS8-4000
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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