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采用三维雷诺平均Ｎ－Ｓ方程程序求解跨音速压气机风扇转子内部流场。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－Ｋｕｔａ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ＮＡＳＡ６７＃跨音速风扇转子的性能曲线，并重点计算最高效率点工况下内部流场。计算结果与实验结果的比较，证明该法可以用来模拟跨音速风扇转子内部流动。
Solving Turbocharged Fan Rotor Internal Flow Field by Using Reynolds Averaged N-S Equation Program. In this program, the governing equations are solved by the finite volume time-explicit method. The independent variables of the equations are selected at the vertices of the control body. A simple H-grid discrete equation is adopted. The discrete algebraic equations are solved by time- Accelerate computational convergence using multiple grids and local time step methods. The Baldwin-Lomax model was used in the program to simulate turbulence effects. The performance curve of the NASA 67 # transonic fan rotor is calculated by this method, and the internal flow field under the highest efficiency point condition is emphatically calculated. Comparing the calculated result with the experimental result, it is proved that this method can be used to simulate the flow inside the transonic fan rotor.