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采用三维Reynold平均Navier-Stokes方程程序求解了一个跨音速低展弦比轴流压气机风扇转子内部流场,并把计算结果和激光测量结果进行了比较。这个程序采用有限体积显式时间推进方法求解控制方程,方程中的自变量选取在控制体顶点,采用简单的H型网格离散方程,离散后的代数方程用两步Runge-Kutta法进行时间推进求解,使用多重网格和当地时间步长方法加速计算收敛。程序中使用了Baldwin-Lomax模型模拟湍流影响。用该方法计算了NASA 67~#音速风扇转子在设计转速下的性能曲线,并重点比较了在堵塞点、最高效率点、临近失速点3个工况下的内部流场。
A three-dimensional Reynold-averaged Navier-Stokes equation was used to solve the flow field inside a transonic low aspect ratio axial fan fan rotor. The calculated results were compared with the laser measurements. This program uses a finite volume time-explicit method to solve the governing equations. The independent variables in the equations are selected at the vertices of the control body. A simple H-grid discrete equation is used. The discrete algebraic equations are time-propelled by the two-step Runge-Kutta method Solve, using multiple grids and local time steps to speed up the calculation of convergence. The Baldwin-Lomax model was used in the program to simulate turbulence effects. The performance curves of the NASA 67 ~ # sonic fan rotor at design speed were calculated by this method, and the internal flow field at three working conditions, ie, the blockage point, the maximum efficiency point and the stalling point, were compared.