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Multi-Point Design Optimization of a Transonic Compressor Blade by Using an Adjoint Method

[+] Author Affiliations
Jiaqi Luo, Chao Zhou

Peking University, Beijing, China

Feng Liu

University of California, Irvine, CA

Paper No. GT2013-95155, pp. V06BT37A030; 13 pages
doi:10.1115/GT2013-95155
From:
  • ASME Turbo Expo 2013: Turbine Technical Conference and Exposition
  • Volume 6B: Turbomachinery
  • San Antonio, Texas, USA, June 3–7, 2013
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5523-2
  • Copyright © 2013 by ASME

abstract

This paper presents the application of a viscous adjoint method to the multi-point design optimization of a rotor blade through blade profiling. The adjoint method requires about twice the computational effort of the flow solution to obtain the complete gradient information at each operating condition, regardless of the number of design parameters. NASA Rotor 67 is redesigned through blade profiling. A single point design optimization is first performed to verify the effectiveness and feasibility of the optimization method. Then in order to improve the performance for a wide range of operating conditions, the blade is redesigned at three operating conditions: near peak efficiency, near stall, and near choke. Entropy production through the blade row combined with the constraints of mass flow rate and total pressure ratio is used as the objective function. The design results are presented in detail and the effects of blade profiling on performance improvement and shock/tip-leakage interaction are examined.

Copyright © 2013 by ASME

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