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The Effects of Wake-Passing Unsteadiness Over a Highly-Loaded Compressor-Like Flat Plate

[+] Author Affiliations
Xavier Ottavy, Stephane Vilmin, Maciek Opoka, Howard Hodson

Cambridge University, Cambridge, UK

Simon Gallimore

Rolls-Royce, Derby, UK

Paper No. GT2002-30354, pp. 273-285; 13 pages
doi:10.1115/GT2002-30354
From:
  • ASME Turbo Expo 2002: Power for Land, Sea, and Air
  • Volume 5: Turbo Expo 2002, Parts A and B
  • Amsterdam, The Netherlands, June 3–6, 2002
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-3610-X | eISBN: 0-7918-3601-0
  • Copyright © 2002 by ASME

abstract

The present study is concerned with wake-induced unsteady effects in axial-compressor blade rows. The goal is to exploit these effects in order to design high-lift blades without increasing the profile loss, as has been achieved for low-pressure turbine blades. In the first part of this paper, the experimental means and the computational fluid dynamics tools are described. The rig features a flat plate that can be subjected to different velocity distributions representative of the suction side of a real compressor blade. Cylindrical bars mounted on a moving system simulate the incoming wakes from the upstream blade row in the compressor. Results are presented for steady flow and for unsteady compressor-like conditions. In all cases, the separation bubble of the steady flow is suppressed by the turbulence that is induced in the boundary layer by the wakes at approximately 10% of the suction side. Its reappearance is then delayed by a region of stable laminar-like flow and low loss, the so-called calming effect that follows the wake-induced patch. The paper describes these phenomena for an example of configuration. It is then shown that it should be possible to increase the lift by 35% while keeping the same level of loss as the initial conventional pressure distribution of the study.

Copyright © 2002 by ASME

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