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Numerical Study on Three-Dimensional Optimization of a Low-Speed Axial Compressor Rotor

[+] Author Affiliations
Chenkai Zhang, Jun Hu, Zhiqiang Wang, Chao Yin, Wei Yan

Nanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu, China

Paper No. GT2014-26431, pp. V02BT45A016; 10 pages
doi:10.1115/GT2014-26431
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

This paper presents numerical optimization of a compressor rotor, to deepen the knowledge of endwall flow in the large-scale axial subsonic compressor, accordingly reduce its endwall loss and improve its aerodynamic performance. With numerical simulation and numerical optimization tools, three-dimensional stacking principle is optimized to improve the design operation point performance for the rotor. Results show that, hub region of the rotor cannot undertake large blade loading; compared to the prototype rotor, obvious aerodynamic performance improvements locate near the hub area, and a certain degree of positive dihedral in this region effectively helps to reduce its flow loss. The effect of “loaded leading edge and unloaded trailing edge” due to positive dihedral was shown, which suppresses flow separation near the trailing edge, consequently obviously reduces the flow loss and largely improves the rotor aerodynamic performance.

Copyright © 2014 by ASME

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