Unsteady Heat Transfer in Stator-Rotor Interaction by Two Equation Turbulence Model PUBLIC ACCESS

[+] Author Affiliations
V. Michelassi, F. Martelli

University of Florence, Florence, Italy

R. Dénos, T. Arts, C. H. Sieverding

Von Karman Institute for Fluid Dynamics, Rhode Saint Genèse, Belgium

Paper No. 98-GT-243, pp. V001T01A058; 15 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


A transonic turbine stage is computed by means of an unsteady Navier-Stokes solver. A two equation turbulence model is coupled to a transition model based on integral parameters and an extra transport equation. The transonic stage is modeled in two-dimensions with a variable span height for the rotor row. The analysis of the transonic turbine stage with stator trailing edge coolant ejection is carried out to compute the unsteady pressure and heat transfer distribution on the rotor blade under variable operating conditions. The stator coolant ejection allows the total pressure losses to be reduced although no significant effects on the rotor heat transfer are found in both the computer simulation and measurements. The results compare favorably with experiments both in terms of pressure distribution and heat transfer around the rotor blade.

Copyright © 1998 by ASME
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