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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.
Taking the NASA-MARK Ⅱ transonic turbine blade and a low-pressure turbine guide vane as an example, the calculation of air-heat coupling is taken into account.Firstly, finite difference air-heat coupled solver was developed, and the direct coupling method was used to transfer the data in the fluid- And AGS algebraic transition model was used to predict the turbulent flow on the leaf surface.Then the turbulence model of NASA-MARKⅡ leaf was tested as an example to show that the AGS model can predict the leaf surface rotation捩 flow process, the predicted blade surface temperature distribution and the convection heat transfer coefficient and experimental values agree well.Finally, the coupled solver was used to calculate the gas-heat coupling of a double-chamber internal cooling and tail-split low-pressure turbine, The thermal load on the blade was analyzed.