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SSME Fuel Preburner Two-Dimensional AnalysisThe durability of the SSME turbine is strongly affected by the temperature profile leaving the preburner. A reacting flow computer model to predict the turbine inlet temperature profile was used. Calculations were made by using a reacting flow code, to assess the sensitivity of the turbine inlet temperature profile to variations in the flow entering the SSME preburner.
Document ID
19850019631
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Thomas J. Vanoverbeke (Glenn Research Center Cleveland, Ohio, United States)
Date Acquired
August 12, 2013
Publication Date
May 1, 1985
Publication Information
Publication: Structural Integrity and Durability of Reusable Space Propulsion Systems
Publisher: National Aeronautics and Space Administration
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: Structural Integrity and Durability of Reusable Space Propulsion Systems
Location: Cleveland, Ohio
Country: US
Start Date: June 4, 1985
End Date: June 5, 1985
Sponsors: National Aeronautics and Space Administration
Accession Number
85N27943
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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