Loss Reduction in Axial-Flow Compressors Through Low-Speed Model Testing

[+] Author and Article Information
D. C. Wisler

Turbomachinery Research Aircraft Engine Group, General Electric Company, Cincinnati, Ohio 45215

J. Eng. Gas Turbines Power 107(2), 354-363 (Apr 01, 1985) (10 pages) doi:10.1115/1.3239730 History: Received January 12, 1984; Online October 15, 2009


A systematic procedure for reducing losses in axial-flow compressors is presented. In this procedure, a large, low-speed, aerodynamic model of a high-speed core compressor is designed and fabricated based on aerodynamic similarity principles. This model is then tested at low speed where high-loss regions associated with three-dimensional endwall boundary layers, flow separation, leakage, and secondary flows can be located, detailed measurements made, and loss mechanisms determined with much greater accuracy and much lower cost and risk than is possible in small, high-speed compressors. Design modifications are made by using custom-tailored airfoils and vector diagrams, airfoil endbends, and modified wall geometries in the high-loss regions. The design improvements resulting in reduced loss or increased stall margin are then scaled to high speed. This paper describes the procedure and presents experimental results to show that in some cases endwall loss has been reduced by as much as 10 percent, flow separation has been reduced or eliminated, and stall margin has been substantially improved by using these techniques.

Copyright © 1985 by ASME
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