Numerical Prediction of Turbine Profile Loss PUBLIC ACCESS

[+] Author Affiliations
L. Xu

Beijing University of Aero- & Astronautics

J. D. Denton

University of Cambridge

Paper No. 90-GT-311, pp. V001T01A096; 8 pages
  • ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Brussels, Belgium, June 11–14, 1990
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7904-7
  • Copyright © 1990 by ASME


A simple numerical method for predicting the profile loss of turbine blades in subsonic and transonic flows is presented. A time marching Euler solver is used to obtain the main flow through the blade passages, the loss due to the surface friction is calculated using an integral boundary layer method, the total mixed out loss is evaluated from the mass flow and momentum balances between the trailing edge plane and an imaginary downstream plane where the flow is uniform. The base pressure acting on the trailing edge of the blade is calculated directly from the inviscid calculation without empirical correlations. The spurious numerical loss in the Euler calculation is separated from the real loss. The rationality of the approach is justified by the agreement of the prediction with a wide range of experimental measurements.

Copyright © 1990 by ASME
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