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Performance of a Highly-Loaded HP Compressor PUBLIC ACCESS

[+] Author Affiliations
W. J. Calvert, R. B. Ginder, I. R. I. McKenzie, D. J. Way

Royal Aerospace Establishment, Pyestock, Farnborough, Hampshire, UK

Paper No. 89-GT-24, pp. V001T01A012; 7 pages
doi:10.1115/89-GT-24
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

A 4-stage axial research compressor, which is representative of the rearmost stages of a highly-loaded military or civil compression system, has been designed and tested at RAE Pyestock. The compressor is of large scale, with extended inter-row gaps, to facilitate the acquisition of detailed aerodynamic data. The unit performed well on test, exceeding its design pressure ratio of 4.0, and achieving a peak polytropic efficiency at design speed of 89%. Flow profiles obtained from area traversing at stator exits are presented and discussed. The measured performance is compared with an S1-S2 calculation incorporating an inviscid-viscous blade-to-blade method.

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

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