Stator-Averaged, Rotor Blade-to-Blade Near-Wall Flow in a Multistage Axial Compressor With Tip Clearance Variation

[+] Author and Article Information
I. N. Moyle, G. J. Walker, R. P. Shreeve

Turbopropulsion Laboratory, Naval Postgraduate School, Monterey, CA 93943

J. Turbomach 114(3), 668-674 (Jul 01, 1992) (7 pages) doi:10.1115/1.2929191 History: Received February 06, 1991; Online June 09, 2008


This paper describes the effect of tip clearance changes on the pressure at the case wall of a second-stage rotor. Wall shear distributions under the rotor tip are also presented. The results show low-pressure areas extending along the rotor suction side but lying away from the blade. Pressure contours indicate the tangential loading at the tip is lower than predicted by two-dimensional calculations; however, the predicted loading is observed between the lowest pressure’s path in the passage and the blade pressure side. The results suggest that a viscous or shearing layer, due to blade-to-wall relative motion, is generated on the blade side of the tip gap, which modifies the inviscid relative flow field and produces an unloading on the blade tip.

Copyright © 1992 by The American Society of Mechanical Engineers
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