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A Numerical Procedure of Three-Dimensional Design Problem in Turbomachinery PUBLIC ACCESS

[+] Author Affiliations
J. Z. Xu, C. W. Gu

Chinese Academy of Sciences, Beijing, China

Paper No. 91-GT-144, pp. V001T01A056; 5 pages
doi:10.1115/91-GT-144
From:
  • ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Orlando, Florida, USA, June 3–6, 1991
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7898-9
  • Copyright © 1991 by ASME

abstract

A numerical method for solving the three–dimensional aerothermodynamic design problem with some type of the Mach number distributions on the blade surfaces is presented. In the usual aerothermodynamic design of a turbomachinery the three–dimensional coordinates of the blade is attained through the stacking of the cascade profiles and may not ensure the desired velocity distribution. To avoid this problem the present method will give new coordinates of the blade according to the required Mach number distribution. The method is based on the pseudostream function formulation and the treatment of the boundary conditions in the design problem is given. The numerical results show that the method is simple and useful in design.

Copyright © 1991 by ASME
This article is only available in the PDF format.

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