Detailed Boundary Layer Measurements on a Transonic Turbine Cascade

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

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), 163-172 (Jan 01, 1992) (10 pages) doi:10.1115/1.2927980 History: Received January 15, 1990; Online June 09, 2008


The boundary layers of a transonic turbine blade have been measured in detail. The full velocity profiles have been measured at a number of stations on both the suction and pressure surfaces, at conditions representative of engine operation, using a Pilot traverse technique and a large-scale (300 mm chord) linear cascade. This information has made it possible to follow the development of the boundary layers, initially laminar, through a region of natural transition to a fully developed turbulent layer. Comparisons with other, less detailed, measurements on the same profile using Pilot traverse and surface-mounted thin films confirm the essential features of the boundary layers.

Copyright © 1992 by The American Society of Mechanical Engineers
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