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Experimental Aerodynamic Analysis Relative to Three High Pressure Ratio Centrifugal Compressors FREE

[+] Author Affiliations
Y. Ribaud

Office National d’Etudes et de Recherches Aérospatiales, Châtillon, France

Paper No. 87-GT-153, pp. V001T01A046; 8 pages
doi:10.1115/87-GT-153
From:
  • ASME 1987 International Gas Turbine Conference and Exhibition
  • Volume 1: Turbomachinery
  • Anaheim, California, USA, May 31–June 4, 1987
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7923-8
  • Copyright © 1987 by ASME

abstract

The test results of three high pressure ratio centrifugal compressors are analyzed. Two of them show one or two discontinuities in the surge line. A careful study of the different experimental parameters indicates the existence of three different operating zones for the rotor. For the low inlet flow coefficients, two recirculations take place in the rotor: one at the inlet and the other at the outlet. For moderate flow coefficients, the outlet recirculation disappears. In these regions, the occurrence of these recirculations is explained and a simple model is given. The inlet recirculation can stabilize the flow if a 2D blade stall occurs but it is not possible in the third zone where the inlet flow coefficient is higher than the critical value.

Copyright © 1987 by ASME
This article is only available in the PDF format.

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