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Industrial Centrifugal Compressors: The Influence of the Impeller Diffusion on the Stage Performance PUBLIC ACCESS

[+] Author Affiliations
Klaus Lüdtke

BORSIG GmbH, Berlin, W.-Germany

Paper No. 89-GT-233, pp. V001T01A092; 9 pages
doi:10.1115/89-GT-233
From:
  • ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Toronto, Ontario, Canada, June 4–8, 1989
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7913-9
  • Copyright © 1989 by ASME

abstract

The meridional convergence of an unshrouded inducer type impeller with 30° backward leaning blades was modified by reducing the exit width by 22%. The vaneless diffuser was changed accordingly, whereas the impeller eye opening was kept constant. Performance curves show that the lower diffusion leads to enhanced surge limit, lower head at increased efficiency. Choke point remains unchanged and the extension of the rotating stall range is reduced. The range of tip speed Machnumbers tested was 0.6 to 1.17.

Test value analysis, broken down into components, is based on the two-zone model impeller exit evaluation procedure detecting clearly the causes of performance map changes.

Copyright © 1989 by ASME
This article is only available in the PDF format.

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