Comparison of Calculated and Experimental Cascade Performance for Controlled-Diffusion Compressor Stator Blading

[+] Author and Article Information
N. L. Sanger

NASA Lewis Research Center, Cleveland, OH 44135

R. P. Shreeve

Naval Postgraduate School, Turbomachinery Laboratory, Monterey, CA 93940

J. Turbomach 108(1), 42-50 (Jul 01, 1986) (9 pages) doi:10.1115/1.3262023 History: Received January 08, 1986; Online November 09, 2009


The midspan section of a previously reported controlled-diffusion compressor stator has been experimentally evaluated in cascade. Measurements were taken over a range of incidence angles for blade chord Reynolds numbers from 470,000 to 690,000. Blade chord length was 12.7 cm, aspect ratio was 2.0, and solidity was 1.67. Measurements included conventional cascade performance parameters as well as blade surface pressures. Computations were made for the inviscid flow field, surface boundary layers, and loss for several of the blade inlet angle conditions, and compared against corresponding data.

Copyright © 1986 by ASME
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