Annulus Wall Boundary-Layer Measurements in a Four-Stage Compressor

[+] Author and Article Information
N. A. Cumpsty

Whittle Laboratory, University of Cambridge, England

J. Eng. Gas Turbines Power 108(1), 2-6 (Jan 01, 1986) (5 pages) doi:10.1115/1.3239881 History: Received December 21, 1984; Online October 15, 2009


There are few available measurements of the boundary layers in multistage compressors when the repeating-stage condition is reached. These tests were performed in a small four-stage compressor; the flow was essentially incompressible and the Reynolds number based on blade chord was about 5 • 104 . Two series of tests were performed; in one series the full design number of blades were installed, in the other series half the blades were removed to reduce the solidity and double the staggered spacing. Initially it was wished to examine the hypothesis proposed by Smith [1] that staggered spacing is a particularly important scaling parameter for boundary layer thickness; the results of these tests and those of Hunter and Cumpsty [2] tend to suggest that it is tip clearance which is most potent in determining boundary-layer integral thicknesses. The integral thicknesses agree quite well with those published by Smith.

Copyright © 1986 by ASME
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