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A Method for Calculating Turbulent Boundary Layers and Losses in the Flow Channels of Turbomachines FREE

[+] Author Affiliations
Lawrence F. Schumann

Lewis Research Center, Cleveland, OH

Paper No. 87-GT-225, pp. V001T01A081; 10 pages
doi:10.1115/87-GT-225
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 interactive inviscid core flow-boundary layer method is presented for the calculation of turbomachine channel flows. For this method, a one-dimensional inviscid core flow is assumed. The end-wall and blade surface boundary layers are calculated using an integral entrainment method. The boundary layers are assumed to be collateral and thus are two-dimensional. The boundary layer equations are written in a stream-line coordinate system. The streamwise velocity profiles are approximated by power law profiles. Compressibility is accounted for in the streamwise direction but not in the normal direction.

Equations are derived for the special cases of conical and two-dimensional rectangular diffusers. For these cases, the assumptions of a one-dimensional core flow and collateral boundary layers are valid. Results using the method are compared with experiment and good quantitative agreement is obtained.

Copyright © 1987 by ASME
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