跨声速轴流压气机特性全三维粘性流动分析

应用Steger-Ｗarming通量分裂技术，将守恒型方程中的流通向量分裂成两部分，应用 NND格式对无粘项进行数值离散，粘性项采用中心差分格式，采用LU-SGS隐式推进迭代建立了跨声速轴流压气机性能及内流场三维N-S方程的高分辨率和高效率的数值方法。数值模拟给出NASA ROTOR37和NASA ROTOR67性能及内流场流动结构。并进一步基于混合平面法建立了多级轴流压气机性能计算模型，详细分析了某一级跨声速轴流压气机性能和内流特性，计算与实验结果比较表明了本模型与方法是可行的和可靠的。

3D Viscous Numerical Investigation On the Overall Aerodynamic

The internal 3D viscous flow fields of the transonic axial-flow compressors are numerically analyzed using a time-marching finite difference method. This calculating method is developed by the Lower-Upper implicit scheme and NND scheme with Steger-Warming flux vectors splitting technique and the centered difference scheme is used for the viscous portion. The mixing plane model is employed to simulate the internal 3D viscous flow fields of multistage axial-flow compressors, the overall performance for NASA ROTOR37, NASA ROTOR67 and one stage compressors are obtained and the internal flow fluids are analyzed in detail. Compared with experimental data, good agreements are found. Those also indicate the model and method are feasible and reliable.