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A model for the Space Shuttle Main Engine High Pressure Oxidizer Turbopump shaft seal systemA model of the High Pressure Oxidizer Turbopump (HPOTP) shaft seal system on the Space Shuttle Main Engine (SSME) is described. The model predicts the fluid properties and flow rates throughout this system for a number of conditions simulating failed seals. The results agree well with qualitative expectations and redline values but cannot be verified with actual data due to the lack thereof. The results indicate that each failure mode results in a unique distribution of properties throughout the seal system and can therefore be individually identified given the proper instrumentation. Furthermore, the detection process can be built on the principle of qualitative reasoning without the use of exact fluid property values. A simplified implementation of the model which does not include the slinger/labyrinth seal combination has been developed and will be useful for inclusion in a real-time diagnostic system.
Document ID
19910046017
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Paxson, Daniel E.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Mechanical Engineering
Meeting Information
Meeting: Annual Health Monitoring Conference for Space Propulsion Systems
Location: Cincinnati, OH
Country: United States
Start Date: November 14, 1990
End Date: November 15, 1990
Accession Number
91A30640
Distribution Limits
Public
Copyright
Other

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