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The Effects of Relative Motion, Blade Edge Radius and Gap Size on the Blade Tip Pressure Distribution in an Annular Turbine Cascade With Clearance FREE

[+] Author Affiliations
G. Morphis, J. P. Bindon

University of Natal, Durban, South Africa

Paper No. 88-GT-256, pp. V001T01A092; 8 pages
doi:10.1115/88-GT-256
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

Flow visualisation and microscopic static pressure measurements were done in the tip clearance region of an annular turbine cascade with a rotating outer casing to simulate the relative motion at the tip of an axial rotor. The effect of relative motion did not have a significant effect on the blade gap pressure distributions. As in previous studies the narrow deep pressure depression on a sharp pressure edge was seen. It was confirmed that the width of the gap separation bubble depends on clearance and a correlation with flow visualisation showed that at the reattachment line there is the expected slight pressure peak. The separation bubble, which is thought to contribute a major part of the leakage loss, was shown to disappear when the pressure surface tip is give a radius of 2.5 gap widths.

Copyright © 1988 by ASME
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