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Experimental and Numerical Analysis of Hub-Corner Stall in Compressor Cascades

[+] Author Affiliations
Eugen Lewin, Dragan Kožulović, Udo Stark

Technische Universität Braunschweig, Braunschweig, Germany

Paper No. GT2010-22704, pp. 289-299; 11 pages
doi:10.1115/GT2010-22704
From:
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 7: Turbomachinery, Parts A, B, and C
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4402-1 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME

abstract

The development of a corner stall has been investigated experimentally and numerically in a rotor hub equivalent compressor cascade operated at increasing loadings (inlet angles). The paper presents some of the experimental and numerical results, including midspan results, contour plots of the total pressure losses, pitchwise averaged total pressure losses and turning angles, flow visualization and, numerically only, visualization of so-called ribbons. These results have been analysed to finally identify an endwall separation vortex, increasing in pitchwise and spanwise direction with increasing loading in a highly complicated and permanently changing endwall topology, as the dominating feature of a developed corner stall.

Copyright © 2010 by ASME

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