Abstract
The aero thermodynamics of the flow field in a cascade with an internal cooling system plays a big role in the whole efficiency of a gas turbine. For an accurate numerical analysis, this transition is one of the main obstacles. In the present work, the γ− Reθ transition model combined with the SST turbulence model is applied to analyze the heat transfer of the Mark II blade. The prediction of the onset of the turbulence layer is proven to be satisfied, while the distribution of the blade surface temperature before the transition is also captured through the model. Meanwhile, it is pointed out that the turbulent kinetic energy might be over-suppressed in the laminar layer before the bypass transition due to the combination of the transition model and the turbulence model. 8 2010 Wiley Periodicals, Inc. Heat Trans Asian Res; Published online in Wiley Online Library (wileyonlinelibrary.com). DOI 10.1002/htj.20331 5
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