Methods 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.
Supersonic turbine design and performance
Joint Conf. of the Gas Turbine Div. and the Fluids Eng. Div. ; 1962 ; San Francisco
1971-01-01
Conference paper
No indication
English
Off-Design Performance of a Multi-Stage Supersonic Turbine
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