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A Quasi-Three-Dimensional Finite Element Solution for Steady Compressible Flow Through Turbomachines PUBLIC ACCESS

[+] Author Affiliations
A. S. Ücer, İ. Yeġen, T. Durmaz

METU, Ankara, Turkey

Paper No. 82-GT-261, pp. V001T01A089; 10 pages
doi:10.1115/82-GT-261
From:
  • ASME 1982 International Gas Turbine Conference and Exhibit
  • Volume 1: Turbomachinery
  • London, England, April 18–22, 1982
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7956-6
  • Copyright © 1982 by ASME

abstract

A quasi-three-dimensional solution method is presented for subsonic flows through turbomachines of arbitrary geometry. Principal equations are based on Wu’s formulation of flow on blade-to-blade and hub-to-shroud surfaces, modified such that the same hub-to-shroud principal equation is used for all types of stream surfaces. Blade-to-blade surfaces are assumed to be surfaces of revolution. A stream function is used as the field variable. The problem is solved by finite element method. An iterative solution is used to find the quasi-three-dimensional solution. Solutions at hub, tip and mid height blade-to-blade surfaces are used to construct a mean hub-to-shroud surface and vice versa, until convergence is obtained. Results indicate that the developed technique is satisfactory for predicting the flow through turbomachine blades.

Copyright © 1982 by ASME
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