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The Influence of Diffuser Vane Leading Edge Geometry on the Performance of a Centrifugal Compressor PUBLIC ACCESS

[+] Author Affiliations
W. W. Clements, D. W. Artt

The Queen’s University of Belfast

Paper No. 89-GT-163, pp. V001T01A068; 7 pages
doi:10.1115/89-GT-163
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 series of experiments was carried out on two turbocharger compressors to determine the influence of pressure face angle, semi-vaneless space suction surface profile and diffuser leading edge radius ratio on stage performance. It was found that whilst compressor performance was virtually unaffected by changes in pressure face angle, performance was sensitive to changes in the semi-vaneless space suction surface profile. Straight wedge diffusers produced higher stage efficiencies than any diffuser with a concave suction surface profile between the leading edge and throat. Optimum stage performance was achieved with diffuser leading edge radius ratios between 1.06 and 1.10.

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

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