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基于非结构化混合网格,采用有限体积法求解了N-S方程,对流项格式为AUSM+,梯度的求解方法为加权最小二乘法,求解器采用LUSGS隐式求解方法,并进行了预处理和网格重排序。与导热方程耦合,搭建了气热耦合平台,采用直接耦合方法,交界面互相传递温度,并且采用能保证通量守恒的面积加权类的插值方式实现数据传递,将γ-Reθt两方程转捩模型应用在流场程序中。通过MARKII叶片4311和5411工况的实验结果进行了验证,结果表明采用转捩模型对压力分布的影响不大,与实验值吻合较好,通过间歇因子的分布可以看出,γ-Reθt模型成功地预测了从层流到湍流的转捩过程,在层流区采用γ-Reθt模型计算的涡粘系数与真实流动情况更加吻合,由于涡粘系数对传热的影响很大,从而有效地提高了边界层的层流区和转捩区的传热计算的精度,得到的温度和换热系数与实验值吻合更好,但是该模型是和SST模型耦合在一起的,由于SST模型的局限性,所以对激波和边界层干扰区域的模拟产生了7%左右的温度误差。
Based on the unstructured mixed meshes, the Navier-Stokes equations are solved by the finite volume method, the convection term is AUSM +, the method of solving the gradient is the weighted least squares method, the solver adopts the LUSGS implicit method, and the pretreatment and grid Reorder. Coupled with the heat conduction equation, a gas-heat coupling platform was set up. The direct coupling method was used to transfer the temperature to each other, and the data was transferred by using an area weighted class interpolation method which can ensure the flux conservation. The γ-Reθt two equations were transferred to the model Application in the flow field program. The experimental results of MARKII blades 4311 and 5411 are validated. The results show that the transition model has little effect on the pressure distribution and is in good agreement with the experimental data. The distribution of intermittent factors shows that the γ-Reθt model is successful Predicts the transition from laminar to turbulent flow. The eddy viscosity coefficient calculated by the γ-Reθt model in the laminar flow area is more consistent with the true flow. Because the eddy viscosity has a great influence on the heat transfer, it effectively increases The accuracy of the heat transfer calculation in the laminar flow region and the transition region of the boundary layer shows that the obtained temperature and heat transfer coefficient are in good agreement with the experimental values. However, this model is coupled with the SST model. Due to the limitation of the SST model , So the simulation of the shock and boundary layer interference area produced a temperature error of about 7%.