CFD Analysis of High Pressure Turbines PUBLIC ACCESS

[+] Author Affiliations
N. Liamis, J.-M. Duboue

SNECMA, Moissy Cramayel, France

Paper No. 98-GT-453, pp. V001T01A105; 11 pages
  • ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 1: Turbomachinery
  • Stockholm, Sweden, June 2–5, 1998
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7862-0
  • Copyright © 1998 by ASME


The purpose of this contribution is to report on the aerodynamical performance calculations carried out around single stage high pressure turbines including rotor blade tip clearance effects. Three different turbine configurations are considered: a low lift case with two different tip gap heights and a high lift case. A multistage approach based on the ONERA-Snecma 3D Navier-Stokes code CANARI is used to investigate the turbine flow behaviour. The computational results are compared with experimental data and with results obtained by single blade row simulations.

Copyright © 1998 by ASME
This article is only available in the PDF format.



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