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Computing Flows In Turbine End BearingsComputer program implements mathematical model of flow through turbine and bearings of high-pressure-oxygen turbopump of Space Shuttle main engine. Intended to determine rate of flow and margin before vaporization in these bearings for various types of geometries. Effects of hydrostatic damper and/or back-pressure seal included. Modified for application to other turbomachines and fluids other than oxygen.
Document ID
19900000667
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Smith, Tyn S. (Rockwell International Corp.)
Date Acquired
August 14, 2013
Publication Date
December 1, 1990
Publication Information
Publication: NASA Tech Briefs
Volume: 14
Issue: 12
ISSN: 0145-319X
Subject Category
Machinery
Report/Patent Number
MFS-29681
Accession Number
90B10667
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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