Compressor Blade Boundary Layers: Part 1—Test Facility and Measurements With No Incident Wakes

[+] Author and Article Information
Y. Dong

Gas Turbine Engineering Division, Ruston Gas Turbines Ltd., Lincoln LN6 7AA, United Kingdom

N. A. Cumpsty

Department of Engineering, Whittle Laboratory, University of Cambridge, Cambridge, CB3 ODY, England

J. Turbomach 112(2), 222-230 (Apr 01, 1990) (9 pages) doi:10.1115/1.2927636 History: Received January 04, 1989; Online June 09, 2008


The boundary layers on compressor blades are sensitive to the conditions at which transition occurs and transition can be affected by the convection of wakes from upstream blade rows. This paper and its companion, Part 2 by the same authors, describes an experiment to study the effect of the moving wakes on the boundary layer of a compressor blade. This paper describes the background and facility devised to introduce wakes together with results obtained on the blades in tests without the wakes present. Part 2 describes the measurements made with the wakes present and presents conclusions for the whole project. Further details of all aspects of the work can be found in Dong (1988).

Copyright © 1990 by The American Society of Mechanical Engineers
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