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A Unified Method for Solving Aerodynamic Cascade Design Problems on an Arbitrary Surface of Revolution FREE

[+] Author Affiliations
X. Y. Sun

College of National Metrology, Hanzhou, Zhejiang, China

Y. Guo, Y. Q. Zhao

Nanhua Power Plant Research Institute, Zhuzhou, Hunan, China

J. Z. Xu

Chinese Academy of Sciences, Beijing, China

Paper No. 88-GT-118, pp. V001T01A049; 7 pages
doi:10.1115/88-GT-118
From:
  • ASME 1988 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Amsterdam, The Netherlands, June 6–9, 1988
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7918-4
  • Copyright © 1988 by ASME

abstract

A method for solving various aerodynamic problems of transonic cascade design is developed, in which the coordinates equation is derived directly by inverting the stream function and the principal equation of the stream function. The corresponding “boundary conditions are obtained similarly. The coordinates equation has the same type property as that of the original equation and the only difference for various aerodynamic problems is the change of the boundary conditions on the cascade surfaces. Numerical results show that this unified method offers a useful tool for transonic cascade design.

Copyright © 1988 by ASME
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