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RESEARCH PAPERS

Compressor Blade Boundary Layers: Part 2—Measurements With Incident Wakes

[+] Author and Article Information
Y. Dong

Gas Turbine Engineering Division, Ruston Gas Turbines Ltd., Lincoln LNG 7AA, United Kingdom

N. A. Cumpsty

Department of Engineering, Whittle Laboratory, University of Cambridge, Cambridge, CB3 ODY, United Kingdom

J. Turbomach 112(2), 231-240 (Apr 01, 1990) (10 pages) doi:10.1115/1.2927637 History: Received January 04, 1989; Online June 09, 2008

Abstract

This paper follows directly from Part 1 by the same authors and describes measurements of the boundary layer on a supercritical-type compressor blade with wakes from a simulated moving upstream blade row convected through the passage. (The blades and the test facilities together with the background are described in Part 1). The results obtained with the wakes are compared to those with none for both low and high levels of inlet turbulence. The transition process and boundary layer development are very different in each case, though the overall momentum thickness at the trailing edge is fairly similar. None of the models for transition is satisfactory when this is initiated by moving wakes.

Copyright © 1990 by The American Society of Mechanical Engineers
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