An Examination of the Contributions to Loss on a Transonic Turbine Blade in Cascade

[+] Author and Article Information
D. J. Mee, M. L. G. Oldfield, T. E. Dickens

Department of Engineering Science, University of Oxford, Oxford, United Kingdom

N. C. Baines

Department of Mechanical Engineering, Imperial College, London, United Kingdom

J. Turbomach 114(1), 155-162 (Jan 01, 1992) (8 pages) doi:10.1115/1.2927979 History: Received January 15, 1990; Online June 09, 2008


Experiments to measure losses of a linear cascade of transonic turbine blades are reported. Detailed measurements of the boundary layer at the rear of the suction surface of a blade and examination of wake traverse data enable the individual components of boundary layer, shock and mixing loss to be determined. Results indicate that each component contributes significantly to the overall loss in different Mach number regimes. Traverses in the near wake of the blade indicate the way in which the wake develops and facilitate examination of the development of the mixing loss.

Copyright © 1992 by The American Society of Mechanical Engineers
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