Gas Turbine Rotor Blade Film Cooling With and Without Simulated NGV Shock Waves and Wakes FREE

[+] Author Affiliations
M. J. Rigby

Rolls-Royce plc, Derby, UK

A. B. Johnson

Schlumberger Cambridge Research, Cambridge, UK

M. L. G. Oldfield

Oxford University, Oxford, UK

Paper No. 90-GT-078, pp. V004T09A017; 8 pages
  • ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration
  • Brussels, Belgium, June 11–14, 1990
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7907-8
  • Copyright © 1990 by ASME


Detailed heat transfer measurements have been made around a film-cooled transonic gas turbine rotor blade in the Oxford Isentropic Light Piston Tunnel. Film cooling behaviour for four film cooling configurations has been analysed for a range of blowing rates both without and with simulated nozzle guide vane (NGV) shock wave and wake passing. The superposition model of film cooling has been employed in analysis of time-mean heat transfer data, while time resolved unsteady heat transfer measurements have been analysed to determine interaction between film-cooling and unsteady shock wave and wake passing. It is found that there is a significant change of film-cooling behaviour on the suction surface when simulated NGV unsteady effects are introduced.

Copyright © 1990 by ASME
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