Effect of the Rear Stage Casing Treatment on the Overall Performance of a Multistage Axial-Flow Compressor PUBLIC ACCESS

[+] Author Affiliations
Yao-Lin Gao

Shenyang Aeroengine Co., Shenyang, Liaoning, China

Ke-Ming Li

Sheyang Aeroengine Research Institute, Shenyang, Liaoning, China

Paper No. 82-GT-110, pp. V001T01A043; 5 pages
  • ASME 1982 International Gas Turbine Conference and Exhibit
  • Volume 1: Turbomachinery
  • London, England, April 18–22, 1982
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7956-6
  • Copyright © 1982 by ASME


This paper discusses the effect of tip treatment in the rear stages of a compressor on the high speed stall margin and efficiency. A nine stage engine compressor was tested in a rig with and without casing treatment on the tip sections of the last three rotors. Another series of tests were conducted on a modified compressor with twisted rotor blades in the rear stages. For both compressors, tip treatment improved high speed surge margin. The first compressor encountered no loss of efficiency with the addition of tip treatment, but the second compressor suffered a loss of efficiency.

Copyright © 1982 by ASME
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