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Conjugate Heat Transfer Numerical Validation and PSE Analysis of Transonic Internally-Cooled Turbine Cascade

[+] Author Affiliations
Peigang Yan, Zhenfeng Wang, Wanjin Han

Harbin Institute of Technology, Harbin, China

Paper No. GT2010-23251, pp. 509-516; 8 pages
doi:10.1115/GT2010-23251
From:
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 4: Heat Transfer, Parts A and B
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4399-4 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME

abstract

Conjugate heat transfer numerical simulation of a transonic internal cooled turbine vane is carried out with a third-order accuracy TVD (Total Variation Diminishing) scheme and multi-block structured grids using the code developed in this paper. Comparison between results of commercial CFD codes with several turbulence models and those of this code show that it is incorrect of computational codes to predict the thermal boundary layer with traditional turbulence models, and that the turbulence models considering transitional phenomenon is able to acquire better accurate heat transfer in thermal boundary layer despite of certain deficiencies yet. The predicted distributions of aerodynamic parameters agree well with the experiments except for the temperature and heat transfer coefficient over the profile surface, which are largely different from the measured data. Results by Star-CD with V2 -F model meet the same problem. Results by the code of this paper are close to those by CFX with K-ω-SST-ML transition model. Adopting transition model of Menter & Langtry (Shear-Stess-Transition model) gives the best results by adjusting the transition onset momentum thickness Reynolds number and the inlet viscosity ratio, especially for the mid part of the suction side where the validation accuracy is of a serious shortage by traditional turbulence model. It is proved in this paper that commercial codes have the ability to simulate transition process and thermal boundary layer accurately, but the designer’s experience is of utmost importance. Robust transition turbulence model should be developed further. PSE stability analysis equation and e-N prediction method are both integrated in this paper. It is concluded that boundary layer stability analysis by PSE method can be applied to the prediction of the transition onset without too many experiences and is able to define the empirical turbulence parameters for the accurate simulation of thermal boundary layer for any airfoil, such as the very important transition onset momentum thickness Reynolds number.

Copyright © 2010 by ASME

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