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Supersonic turbine design and performanceMethods for designing supersonic stator and rotor blading corrected for boundary layer displacement thickness are summarized. Computer programs based on these methods have been reported in NASA publications. Analytical blade losses for blading of this type are presented and design limitations resulting from consideration of flow separation and supersonic starting are discussed. In addition, a summary of the experimental performance of a single-stage turbine designed by these methods is given.
Document ID
19720005134
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Goldman, L. J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
January 1, 1971
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TM-X-67961
E-6671
Report Number: NASA-TM-X-67961
Report Number: E-6671
Meeting Information
Meeting: Joint Conf. of the Gas Turbine Div. and the Fluids Eng. Div.
Location: San Francisco
Start Date: March 26, 1962
End Date: March 30, 1962
Sponsors: ASME
Accession Number
72N12783
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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