NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login

Press Enter or click the Search button to begin your search.

Back to Results
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
ISSN: 0145-319X
Report Number: MFS-29681
Accession Number
90B10667
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Available Downloads

There are no available downloads for this record.

Related Records

There are no records associated with this record.
No Preview Available