基于非结构网格的涡轮气热耦合数值方法研究

Study of Turbine Conjugate Heat Transfer Simulation Based on Unstructured Grids

利用课题组自主开发的三维非结构隐式N-S计算软件CU_Turbo,采用气热耦合计算方法,对MarkⅡ内冷径向涡轮导向叶片、带气膜冷却涡轮导叶MT1的流场和温度场进行了数值模拟。计算过程中,隐式时间推进中Jacobi ans矩阵采用对Roe通量的一种近似方法求解。结果表明,计算值与试验值吻合良好,验证了气热耦合计算方法的实用性和有效性,为涡轮工程设计提供了一种新的计算分析方法;涡轮叶片通道内附面层的不同流动状态及气膜冷却,对当地换热都有很大的影响。

This paper describes an attempt to predict the aerodynamic pressure loading and heat transfer of two cases with an unstructured Navier-Stokes flow solver, which include a NASA turbine vanes-MarkII and NG MT1. A three-dimensional Reynolds-averaged Navier-Stokes unstructured flow solver, referred to as CU Turbo, has been modified to solve the governing equations in the flow field and a thermal diffusion equa- tion inside the solid region in a coupled manner. During implicit time iterative, an approximate method of Roe flux is used for finding the Jacobians matrix. The results showed that the numerical simulation results were agreement well with the experimental values. The results verified the feasibility and effectiveness of the code. So the code provides a new method of calculation and analysis for the engineering design of tur- bine; flow condition in boundary layer and film cooling have great impacts on the local heat transfer in tur- bine vane channels.