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Influence of Sweep on the 3D Shock Structure in an Axial Transonic Compressor

[+] Author Affiliations
Jörg Bergner, Stephan Kablitz, Dietmar K. Hennecke

Technische Universität Darmstadt, Darmstadt, Germany

Harald Passrucker, Erich Steinhardt

MTU Aero Engines GmbH, München, Germany

Paper No. GT2005-68835, pp. 343-352; 10 pages
doi:10.1115/GT2005-68835
From:
  • ASME Turbo Expo 2005: Power for Land, Sea, and Air
  • Volume 6: Turbo Expo 2005, Parts A and B
  • Reno, Nevada, USA, June 6–9, 2005
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4730-6 | eISBN: 0-7918-3754-8
  • Copyright © 2005 by ASME

abstract

To improve the understanding of how sweep affects the 3D shock structure and the shock-vortex interaction, two transonic compressor bladings are measured with a 3D Laser-2-Focus setup, and the flow is analyzed for comparable operating conditions. Rotor 1 features radially stacked profiles, while rotor 3 introduces forward sweep. Performance comparisons of these rotors [1] indicated that forward sweep, as introduced in this design, has a beneficial effect on performance and stall margin. The detailed experimental analysis of the 3D shock structure and the influence of tip leakage vortex interaction at design speed is the scope of this paper.

Copyright © 2005 by ASME

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