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

[+] Author Affiliations
I. K. Jennions

General Electric Company, Cincinnati, OH

P. Stow

Rolls-Royce Limited, Derby, England

Paper No. 85-IGT-63, pp. V001T02A020; 8 pages
doi:10.1115/85-IGT-63
From:
  • ASME 1985 Beijing International Gas Turbine Symposium and Exposition
  • Volume 1: Aircraft Engine; Turbomachinery
  • Beijing, People’s Republic of China, September 1–7, 1985
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7942-9
  • Copyright © 1985 by ASME

abstract

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 on from previous publications on the system in which the mathematical analysis and computerised 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 it is dominated by centrifugal effects. In both examples the effects of circumferential non-uniformities are detailed and discussed.

Copyright © 1985 by ASME
This article is only available in the PDF format.

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