考虑转捩的气冷涡轮气热耦合仿真

以NASA-MARKⅡ跨音速涡轮叶片以及某低压涡轮导叶为例进行了考虑转捩的气热耦合计算. 首先开发了有限差分气热耦合求解器,采用直接耦合方法进行流固区域的数据传递,并采用AGS代数转捩模型来预测叶片表面的转捩流动现象. 然后以NASA-MARKⅡ叶片的5411号试验工况为例对该转捩模型进行了验证,对比表明AGS模型能够预测叶片表面的转捩流动过程,所预测的叶片表面温度分布与对流换热系数分布和实验值吻合较好. 最后采用该耦合求解器对某双腔内冷以及尾缘劈缝的低压涡轮进行气热耦合计算,对叶片的热负荷进行了分析. 

Coupled Heat Transfer Simulations Considering Transition Flow Around Vane Surface

Coupled heat transfer (CHT) simulations taking account of transition flow around vane surfaces are carried out in this research. First, a coupled solver with finite difference method was developed to compute the heat transfer, and the direct coupling method was employed to combine the N-S equation solver in the flow passage and the heat transfer module in the solid domain. The modified Abu-Ghannam and Shaw (AGS) algebraic transition model was used to predict the transition flow around the vane surfaces. Then, coupled heat transfer simulation was carried out and verified through testing the 5411 run of NASA-MARKⅡ vane, a high-pressure turbine vane. The comparison between the numerical results and the tested ones has been shown that the AGS transition model is able to predict the transition model process in the boundary layer, and that the predicted vane thermal loads by such model are closer to the tested ones than those by full turbulence model. Finally the developed solver has been applied to the CHT simulations of a low-pressure air-cooled turbine with two cooling air channels and a slut in the trailing edge, and its vane thermal load could be analytically obtained.