Supersonic Turbine Design and Performance PUBLIC ACCESS

[+] Author Affiliations
L. J. Goldman

National Aeronautics and Space Administration, Lewis Research Center, Cleveland, OH

Paper No. 72-GT-63, pp. V001T01A062; 10 pages
  • ASME 1972 International Gas Turbine and Fluids Engineering Conference and Products Show
  • ASME 1972 International Gas Turbine and Fluids Engineering Conference and Products Show
  • San Francisco, California, USA, March 26–30, 1972
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7981-8
  • Copyright © 1972 by ASME


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.

Copyright © 1972 by ASME
Topics: Design , Turbines
This article is only available in the PDF format.



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