中文摘要：

采用CFX商用软件对NASA-MarkⅡ高压燃气涡轮5411工况进行气热耦合计算,着重分析各种湍流模型对转捩流动区域的预测能力,与实验结果比较,k-ω-shear-stress-transport（SST）-Gamma-Theta湍流模型计算结果与实验结果吻合较好.另外,自编耦合计算程序对相同工况进行气热耦合计算,湍流模型采用Baldwin-Lomax（B-L）代数模型,结果说明,除转捩区域外,B-L模型对叶片表面其余位置的计算结果较准确.应用ANSYS商用软件进行热应力分析,结果表明,涡轮叶片温度场求解结果对叶片内部热应力分布具有显著影响.

英文摘要：

The commercial code CFX was used to simulate NASA-MarkⅡ high pressure air-cooled gas turbine under work condition of Run 5411.The simulation ability of different turbulence models for the transition flow region was researched in this paper.As compared with the experimental results,k-ω-shear-stress-transport（SST）-Gamma-Theta turbulence model results were more accurate.In addition,the compiled code employed the Baldwin-Lomax（B-L） algebra model to simulate the same computation model.The results show that the results of B-L model are accurate apart from some temperature error in the transition region.ANSYS can be applied to analyze the thermal stress of solid blade and the results of Von Mises stress show that the temperature results have a great effect on the results of blade thermal stress.