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Temperature Rise in the Multistage Axial Flow Compressor During Rotating Stall and Surge FREE

[+] Author Affiliations
Katerina Nácovská

CKD Kompresory, Praha, Czechoslovakia

Paper No. 88-GT-323, pp. V001T01A109; 9 pages
doi:10.1115/88-GT-323
From:
  • ASME 1988 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Amsterdam, The Netherlands, June 6–9, 1988
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7918-4
  • Copyright © 1988 by ASME

abstract

An experimental investigation of rotating stall and surge was carried out on a four stage axial flow compressor. Results of flow and blade temperature measurements in the compressor are presented. Internal temperature levels during rotating stall and surge are considerably higher than those obtained during unstalled compressor operation. In the pure rotating stall regime, the temperature is almost identical in all compressor stages and depends only on rotor speed and mass flow rate. During surge, the highest temperature is found at the tip diameter prior to the first stage rotor. The absolute level depends on rotor speed, mass flow rate (i.e. throttle position) and on the number of compressor stages. A model of the temperature changes in the multistage compressor during the surge cycle has been derived from the experiments.

Copyright © 1988 by ASME
This article is only available in the PDF format.

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