中文摘要：

为节省涡轮叶栅气热耦合数值模拟时间及提高计算结果准确度，将应用较为广泛的迪图斯-贝尔特和格尼林斯基管内对流换热系数准则武应用于NASA—MarkⅡ高压燃气气冷涡轮叶栅气热耦合换热计算中，换热系数准则式引入温度差和入口效应等考虑涡轮内冷腔几何及工况的修正因子．采用商用软件CFX11．0的不同湍流模型进行数值模拟计算，计算结果表明，在气冷涡轮叶片的冷却通道、冷却孔等位置，采用经过修正的对流换热系数实验准则式能够得出与实验结果较为吻合的计算结果．准则式的应用，省略了冷却通道流体域求解过程，避免了湍流模型对冷却通道流体的计算误差和冷却通道湍流特性边界条件不确切给定带来的结果误差．

英文摘要：

To save the calculating time and improve the precision of results, Dittus-Boelter criteria formula and Gnielinski criteria formula are adopted in the calculation of conjugate heat transfer analysis for the NASA- MarkⅡ high pressure air-cooled gas turbine. Considering of the geometry and work conditions of inner-cooling channels, and by correcting the temperature difference coefficient and the entry effect coefficient, the commercial software CFX11.0 is used to simulate NASA-MarkⅡ high pressure air-cooled gas turbine by different turbulence models. The simulation results agree well with the experimental ones. In addition, because of the application of heat transfer coefficient criteria formulas, the calculation of inner-cooling channel fluid domain, the conjugate errors of inner-cooling channel fluid domain and the solid blade domain with different turbulence models and the calculation errors of uncertain inner-cooling channel turbulence characteristic boundary conditions, are all avoided.