Experimental Investigation of Supersonic Turbine Performance PUBLIC ACCESS

[+] Author Affiliations
John W. Kurzrock

Sundstrand Advanced Technology Group, Rockford, IL

Paper No. 89-GT-238, pp. V001T01A094; 7 pages
  • ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Toronto, Ontario, Canada, June 4–8, 1989
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7913-9
  • Copyright © 1989 by ASME


This paper presents the performance obtained from testing single-stage, full-admission, axial supersonic turbine configurations. A matrix of four nozzle and two rotor blade configurations was evaluated. Turbine pressure ratios were varied from 33 to 140 for velocity ratios of 0.2 to 0.5. The test results indicate that constant-channel width and variable-channel width rotor blading give comparable performance. Optimal nozzle and blade configurations yielded turbine efficiencies of 77 percent.

Copyright © 1989 by ASME
Topics: Turbines
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