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Stator Exit Flow Fields in the Multistage Environment of an Axial Compressor FREE

[+] Author Affiliations
M. Jung, J. Eikelmann

Ruhr-Universität Bochum, Germany

Paper No. 95-GT-165, pp. V001T01A036; 11 pages
doi:10.1115/95-GT-165
From:
  • ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Houston, Texas, USA, June 5–8, 1995
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7878-1
  • Copyright © 1995 by ASME

abstract

Detailed measurements have been taken at the exit of the four stages of an axial compressor of industrial design for two operating points. Pneumatic probes and fast response pressure transducers have been used. Special attention is paid to the endwall flow near hub and casing and the stage-by-stage development of this region of high loss.

The steady state investigations show the leakage flow to be the dominant feature of the endwall region near the hub. This is also apparent near the casing for the unshrouded and adjustable stator blades. At the hub this flow phenomenon intensifies axially from stage-to-stage and with increased aerodynamic loading.

Variations in geometry of the radial clearance at the casing have been investigated to understand the structure and effects of the leakage flow.

Unsteady state flow measurements confirm the steady state results. Further, the endwall flow and especially the leakage vortex are detected as regions of high periodic fluctuations.

Copyright © 1995 by ASME
This article is only available in the PDF format.

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