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Effect of Maximum Camber Location on Aerodynamics Performance of Transonic Compressor Blades

[+] Author Affiliations
N. X. Chen, H. W. Zhang, Y. J. Xu, W. G. Huang

Chinese Academy of Sciences, Beijing, China

H. Du

Shenyang Aeroengine Research Institute, Shenyang, China

Paper No. GT2005-68541, pp. 1117-1125; 9 pages
doi:10.1115/GT2005-68541
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

It is well known that to increase rotational velocity is one of the effective measures to increase total pressure ratio. With increasing velocity, under the condition of transonic flow, the obvious effect of maximum camber location on aerodynamics performance of compressor blades especially in the supersonics zone can be found. In order to reduce the blade losses and to improve the blade design methodology it is necessary to study this complex flow mechanism. This paper describes only the influence of relative maximum camber location on aerodynamics performance, mainly adiabatic efficiency. As an example an axial fan was designed and calculated by the methodologies developed at the Institute of Engineering Thermophysics, Chinese Academy of Sciences.

Copyright © 2005 by ASME

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