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The Computation of Transonic Flow Through Two-Dimensional Gas Turbine Cascades FREE

[+] Author Affiliations
P. W. McDonald

Pratt & Whitney Aircraft, East Hartford, CT

Paper No. 71-GT-89, pp. V001T01A089; 7 pages
doi:10.1115/71-GT-89
From:
  • ASME 1971 International Gas Turbine Conference and Products Show
  • ASME 1971 International Gas Turbine Conference and Products Show
  • Houston, Texas, USA, March 28–April 1, 1971
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7982-5
  • Copyright © 1971 by ASME

abstract

Steady transonic flow through two-dimensional gas turbine cascades is efficiently predicted using a time-dependent formulation of the equations of motion. An integral representation of the equations has been used in which subsonic and supersonic regions of the flow field receive identical treatment. Mild shock structures are permitted to develop naturally without prior knowledge of their exact strength or position. Although the solutions yield a complete definition of the flow field, the primary aim is to produce airfoil surface pressure distributions for the design of aerodynamically efficient turbine blade contours. In order to demonstrate the accuracy of this method, computed airfoil pressure distributions have been compared to experimental results.

Copyright © 1971 by ASME
This article is only available in the PDF format.

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