Abstract: The internal flow field of NASA Lewis Rotor 67 was numerically analyzed using a fast full 3-D viscous flow calculating method with multigrid acceleration technique This practical engineering-oriented method was developed based on a new Lower-Upper implicit scheme and a fourth-order high resolution MUSCL TVD scheme A wall-function method was employed to effectively reduce the computational effort Simple zero-equation turbulence model was adopted to closure the Reynolds-averaged Navier-Stokes equations Compared with the results obtained from experimental data, these solutions demonstrate both the efficiency and accuracy needed by practical applications

Key words: Transonic compressor;Axial flow fan;Numerical calculation;Multi-grid meth?

摘要： 采用一种快速求解三维粘性流场的计算方法求解跨声速压气机风扇转子内部流场。该方法以LU型隐式格式和MUSCLTVD迎风格式为基础 ,结合壁面函数方法和简单的混合长度湍流模型 ,使用多重网格迭代加速收敛技术 ,对三维可压缩雷诺平均N S方程进行求解。计算得到了NASALewis 6 7跨声速、低展弦比轴流风扇转子的性能曲线 ,并重点分析了最高效率点工况和近失速工况下的内部流场。计算与实验结果的对比表明 ,此方法能快速得到三维粘性流场的流动特性且计算精度较高 ,可用来模拟跨声速风扇转子内部流动

关键词: 跨音速压气机;轴流风扇;数值计算;多重网格方法