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Three-Dimensional Calculation of Wall Boundary Layer Flows in Turbomachines FREE

[+] Author Affiliations
W. L. Lindsay

Pratt & Whitney, Quebec, Canada

H. B. Carrick

I. C. I., Middlesbrough, UK

J. H. Horlock

Open University, Milton Keynes, UK

Paper No. 87-GT-82, pp. V001T01A024; 10 pages
doi:10.1115/87-GT-82
From:
  • ASME 1987 International Gas Turbine Conference and Exhibition
  • Volume 1: Turbomachinery
  • Anaheim, California, USA, May 31–June 4, 1987
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7923-8
  • Copyright © 1987 by ASME

abstract

An integral method of calculating the three-dimensional turbulent boundary layer development through the blade rows of turbomachines is described. It is based on the solution of simultaneous equations for

(i) & (ii) the growth of streamwise and cross-flow momentum thicknesses;

(iii) entrainment;

(iv) the wall shear stress;

(v) the position of maximum cross-flow.

The velocity profile of the streamwise boundary layer is assumed to be that described by Coles. The cross-flow profile is assumed to be the simple form suggested by Johnston, but modified by the effect of bounding blade surfaces, which restrict the cross-flow. The momentum equations include expressions for “force-defect” terms which are also based on secondary flow analysis.

Calculations of the flow through a set of guide vanes of low deflection show good agreement with experimental results; however, attempts to calculate flows of higher deflection are found to be less successful.

Copyright © 1987 by ASME
This article is only available in the PDF format.

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