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Simulation of Three-Dimensional Viscous Flow Within a Multistage Turbine PUBLIC ACCESS

[+] Author Affiliations
John J. Adamczyk

National Aeronautics and Space Administration, Cleveland, OH

Mark L. Celestina, Tim A. Beach

Sverdrup Technologies, Inc., Cleveland, OH

Mark Barnett

United Technologies Research Center, Hartford, CT

Paper No. 89-GT-152, pp. V001T01A059; 13 pages
doi:10.1115/89-GT-152
From:
  • ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Toronto, Ontario, Canada, June 4–8, 1989
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7913-9
  • Copyright © 1989 by ASME

abstract

This work outlines a procedure for simulating the flow field within multistage turbomachinery which includes the effects of unsteadiness, compressibility, and viscosity. The associated modeling equations are the average passage equation system which governs the time-averaged flow field within a typical passage of a blade row embedded within a multistage configuration. The results from a simulation of a low aspect ratio stage and one-half turbine will be presented and compared with experimental measurements. It will be shown that the secondary flow field generated by the rotor causes the aerodynamic performance of the downstream vane to be significantly different from that of an isolated blade row.

Copyright © 1989 by ASME
This article is only available in the PDF format.

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