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RESEARCH PAPERS

Boundary Layer Optimization for the Design of High Turning Axial Flow Compressor Blades

[+] Author and Article Information
K. D. Papailiou

Low Speed Section, Turbomachinery Laboratory, von Karman Institute, Rhode Saint Genese, Belgium

J. Eng. Power 93(1), 147-154 (Jan 01, 1971) (8 pages) doi:10.1115/1.3445387 History: Received January 30, 1970; Online July 14, 2010

Abstract

An optimization method, based on Le Foll’s boundary layer theory and on Goldstein’s conformal mapping method is described. The parameters of optimization are circulation per blade and absolute losses. The problem is treated as an inverse problem (i.e., the best blading is found starting from the flow conditions imposed). The performance of a highly loaded compressor cascade, designed according to the method presented and tested in a low speed wind tunnel, is compared with the theoretical predictions. Some discrepancies exist which are due to the influence of flow convergence and blade curvature. A modification of the method to take into account these effects is discussed.

Copyright © 1971 by ASME
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