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Effect of Stage Loading on Endwall Flows in an Axial Flow Compressor Rotor FREE

[+] Author Affiliations
N. Sitaram

Indian Institute of Technology, Madras, India

Paper No. 88-GT-111, pp. V001T01A048; 7 pages
doi:10.1115/88-GT-111
From:
  • ASME 1988 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Amsterdam, The Netherlands, June 6–9, 1988
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7918-4
  • Copyright © 1988 by ASME

abstract

This paper reports results from investigations conducted to determine the effect of stage loading on endwall flows in a low speed axial flow compressor. These investigations consisted of two sets of measurements. The first set consisted of radial tranverse of flow properties at the rotor inlet and exit, at five flow coefficients. These measurements are used to determined the boundary layer integral parameters. The displacement thicknesses at the rotor hub and tip agree reasonably well with Smith’s (1970) correlation for multistage axial compressors. The second set consisted of measurements of static pressures on the rotor blade at four flow coefficients. From these measurements lift coefficient is determined. Also loss of lift coefficient near the tip is calculated and is attributed mainly to the tip leakage flows.

Copyright © 1988 by ASME
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