叶轮机械转动叶片上三维可压边界层微分方程的求解方法

A METHOD OF PREDICTING 3-D COMPRESSIBLE BOUNDARY LAYER ON THE ROTATING BLADE OF TURBOMACHINERY

本文应用非正交曲线坐标,在叶轮机械转动叶片上建立了三维边界层的微分方程及其求解方法。对一个压气机转子叶片的压力面和吸力面上的三维边界层进行了计算,结果表明,与实验结果比较符合。

Taking account of the rotation effect of the rotor in turbomachinery, 3-D boudary layer differential equations are established in terms of non-orthogonal curvilinear coordinates and an algebra eddy turbulence model is adopted in present study. If boundary conditions and suitable initial conditions are given, the parameters at every point inside the boundary layer can be obtained by solving the parabolic differential equation after discretization is carried out by finite difference method. The results of the calculation of 3-D bountary layer on pressure and suction surface of the compressor rotor blade show that the numerical solution is in good agreement with the experimental data.