The Influence of Tip Clearance, Stage Loading, and Wall Roughness on Compressor Casing Boundary Layer Development

[+] Author and Article Information
J. L. Bettner

Detroit Diesel Allison, Division General Motors Corporation, Indianapolis, Ind. 46206

C. Elrod

Technology Branch, Turbine Engine Division, Aeropropulsion Laboratory, Wright Patterson AFB, Dayton, Ohio

J. Eng. Power 105(2), 280-287 (Apr 01, 1983) (8 pages) doi:10.1115/1.3227413 History: Received December 14, 1981; Online September 28, 2009


An experimental program was conducted in a highly loaded, single-stage, low-speed research compressor that featured variations in blade tip clearances, shroud wall roughness, and stage loading levels. The results showed that tip clearances and stage loading levels exerted a very strong influence on casing boundary layer growth. Shroud wall roughness not only showed some effect on casing boundary layer development, but also influenced stage stall margin. The results point out the need to understand the basic flow processes that occur if realistic mathematical models are to be developed so that casing boundary layer development and its influence on compressor stage performance can be accurately predicted.

Copyright © 1983 by ASME
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