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The Effect of Coolant Flow on the Efficiency of a Transonic HP Turbine Profile Suitable for a Small Engine PUBLIC ACCESS

[+] Author Affiliations
G. W. Michel

Rolls-Royce Limited, Bristol, UK

F. H. Kost

DFVLR-AVA Gottingen, Institut fur Experimentelle Stromungs-Mechanik, Gottingen, West Germany

Paper No. 82-GT-63, pp. V001T01A024; 10 pages
doi:10.1115/82-GT-63
From:
  • ASME 1982 International Gas Turbine Conference and Exhibit
  • Volume 1: Turbomachinery
  • London, England, April 18–22, 1982
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7956-6
  • Copyright © 1982 by ASME

abstract

A gas turbine blade with a very thick trailing edge (thickness/throat = 22 percent) has been tested in a plane cascade over the exit Mach number range of 0.7 to 1.3. To investigate the effect of cooling air on the aerodynamic performance, tests have been carried out for the solid blade and by blowing air through slots in the trailing edge of the profile. The results indicate the sensitivity of cascade performance to trailing edge geometry and flow conditions. Especially in the subsonic regime the slotted blades gave an unusual loss reduction which should be attributed to a change in the unsteady separation process at the trailing edge.

Copyright © 1982 by ASME
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