The Importance of Circumferential Non-uniformities in a Passage-Averaged Quasi-Three-Dimensional Turbomachinery Design System

[+] Author and Article Information
I. K. Jennions

Aero Design Methods, General Electric Company, Cincinnati, OH 45215

P. Stow

Theoretical Science Group, Rolls-Royce Limited, Derby DE2 8BJ, England

J. Eng. Gas Turbines Power 108(2), 240-245 (Apr 01, 1986) (6 pages) doi:10.1115/1.3239894 History: Received May 31, 1985; Online October 15, 2009


The purpose of this paper is to show, for both rotating and non-rotating blade rows, the importance of including circumferential non-uniform flow effects in a quasi-three-dimensional blade design system. The paper follows from previous publications on the system in which the mathematical analysis and computerized system are detailed. Results are presented for a different stack of the nozzle guide vane presented previously and for a turbine rotor. In the former case it is again found that the blade force represents a major contribution to the radial pressure gradient, while for the rotor the radial pressure gradient is dominated by centrifugal effects. In both examples the effects of circumferential non-uniformities are detailed and discussed.

Copyright © 1986 by ASME
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