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Application of Optimisation Techniques for New High-Turning Axial Compressor Profile Topology Design

[+] Author Affiliations
Oleg V. Komarov, Viacheslav A. Sedunin, Vitaly L. Blinov

Ural Federal University, Yekaterinburg, Russia

Paper No. GT2014-25379, pp. V02BT39A008; 9 pages
doi:10.1115/GT2014-25379
From:
  • ASME Turbo Expo 2014: Turbine Technical Conference and Exposition
  • Volume 2B: Turbomachinery
  • Düsseldorf, Germany, June 16–20, 2014
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4561-5
  • Copyright © 2014 by ASME

abstract

An example of optimisation of high-turning outlet guide vanes for subsonic compressor stage is implemented in a new approach for blade profile topology. This topology includes types of curves on PS, SS, the number of control points and the distribution law, where several coefficients are implemented as function of the upstream flow. This functional law is defined during optimisation procedures for profiles with different parameters (Mach, inlet angle, turning angle, solidity) and further correlation analysis. As a result an 8 degree gain in turning angle for last stage guide vane is achieved. Also possible design is provided for a 12 degree gain in turning angle with higher pressure losses on 20% (relatively).

Copyright © 2014 by ASME

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