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Hotfire testing of a SSME HPOTP with an annular hydrostatic bearingA new fluid film bearing package has been tested in the SSME High Pressure Oxygen Turbopump (HPOTP). This fluid film element functions as both the pump end bearing and the preburner pump rear wear ring seal. Most important, it replaces a duplex ball bearing package which has been the primary life limiting component in the turbopump. The design and predicted performance of the turbopump are reviewed. Results are presented for measured pump and bearing performance. The most significant results were obtained from proximity probes located in the bearing bore which revealed large subsynchronous precession at 10 percent of shaft speed during engine start which subsided prior to mainstage power levels and reappeared during engine shutdown at equivalent power levels below 65 percent of nominal. This phenomenon has been attributed to rotating stall in the diffuser. The proximity probes also revealed the location of the bearing in the bore for different operating speeds. Pump vibration characteristics were improved as compared to pumps tested with ball bearings. After seven starts and more than 700 seconds of testing, the pump showed no signs of performance degradation.
Document ID
19930066131
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Nolan, Steven A.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Hibbs, Robert I.
(Rockwell International Corp. Rocketdyne Div., Canoga Park, CA, United States)
Genge, Gary G.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
August 16, 2013
Publication Date
June 1, 1993
Subject Category
Mechanical Engineering
Report/Patent Number
AIAA PAPER 93-2356
Meeting Information
Meeting: AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit
Location: Monterey, CA
Country: United States
Start Date: June 28, 1993
End Date: June 30, 1993
Sponsors: AIAA, ASME, ASEE, SAE
Accession Number
93A50128
Distribution Limits
Public
Copyright
Other

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