A Numerical Modeling of Endwall and Tip-Clearance Flow of an Isolated Compressor Rotor

[+] Author and Article Information
C. Hah

Corporate Research and Development, General Electric Company, Schenectady, N.Y. 12301

J. Eng. Gas Turbines Power 108(1), 15-21 (Jan 01, 1986) (7 pages) doi:10.1115/1.3239863 History: Received December 27, 1984; Online October 15, 2009


The current study is aimed at developing and appraising a numerical method for the development of endwall boundary layers through tip-clearances and their effect on the performance of an isolated compressor rotor. The Reynolds-averaged Navier-Stokes equation is solved for the entire flow field in elliptic form. The relative flow is computed on the generalized coordinates fixed on the rotor. Comparison between the numerical results and experimental data indicates that the complex three-dimensional viscous flow phenomena inside the tip region are properly predicted.

Copyright © 1986 by ASME
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