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Experimental Investigation of a Stall Prediction System Using a Transonic Multistage Compressor

[+] Author Affiliations
Tomofumi Nakakita

Ishikawajima-Harima Heavy Industries Company, Ltd., Tokyo, Japan

Masahiro Kurosaki

Ishikawa National College of Technology, Kahoku, Ishikawa, Japan

Yukio Kamiyoshihara

Japan Aircraft Development Corporation, Tokyo, Japan

Paper No. GT2007-28199, pp. 67-76; 10 pages
  • ASME Turbo Expo 2007: Power for Land, Sea, and Air
  • Volume 6: Turbo Expo 2007, Parts A and B
  • Montreal, Canada, May 14–17, 2007
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4795-0 | eISBN: 0-7918-3796-3
  • Copyright © 2007 by ASME


This paper describes the test results of a stall prediction system using a transonic multistage axial compressor. The test results show that there is a clear relationship between the stall margin and the stall-warning index measured at the first stage. The stall warning index is derived from auto correlation of casing wall pressure signals above the rotor tip. In the tests, the compressor installed with pressure transducers on the casing wall near the leading edges of the first three rotors was forced to stall while operating at a constant speed by closing the discharge valve. The test results where the stator vane settings of the first three stages were changed show that load distribution among stages does not have significant effects on the stall margin vs. stall-warning index relationship. Using some smoothing technique, undesired time variation of the stall-warning index can be reduced to the level necessary for practical active stall control with allowable response time delay.

Copyright © 2007 by ASME
Topics: Compressors



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