Unsteady Aerodynamic and Heat Transfer Processes in a Transonic Turbine Stage

[+] Author and Article Information
D. A. Ashworth

Rolls-Royce Ltd., Derby, England

J. E. LaGraff

Syracuse University, Syracuse, N.Y.

D. L. Schultz, K. J. Grindrod

The University of Oxford, England

J. Eng. Gas Turbines Power 107(4), 1022-1030 (Oct 01, 1985) (9 pages) doi:10.1115/1.3239806 History: Received January 07, 1985; Online October 15, 2009


The effect of the interaction of the wake from a nozzle guide vane with the rotor may be simulated in part by means of a stationary rotor and a moving wake system. This technique is applied to a transonic rotor blade cascade, and the unsteady measurements of surface pressure and heat transfer rate are compared with baseline data obtained without the wake interaction. The wake-rotor interaction results in a change in inlet incidence angle and this effect is also examined in the steady-state case. It is found that the shock waves from the moving wake system have a major effect on the instantaneous heat transfer rates.

Copyright © 1985 by ASME
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