多级轴流压气机全工况特性数值模拟

采用一种快速求解三维粘性流场的计算方法求解某多级轴流压气机内部流场及全工况特性。该方法以ＬＵ－ＳＧＳ－ＧＥ隐式格式和 ＭＵＳＣＬ ＴＶＤ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Ｎａｖｉｅ－Ｓｔｏｋｅｓ方程进行求解．叶列间参数的传递采用混合平面方法并应用了微机网络并行计算技术．首先对一个五排压气机（进口导叶加两级）进行了全工况特性计算，并对计算结果做了详细分析．然后对前三排（进口导叶加一级）进行了全工况特性计算并与五排联赛的计算结果进行了对比，对多级环境对单级性能的影响机理做了初步探讨。

NUMERICAL SIMULATION OF THE OVERALL AERODYNAMIC PERFORMANCE OF MULTI-STAGE AXIAL-FLOW COMPRESSOR

The internal flow field of a multi-stage axial-flow compressor was analyzed using a fast full 3-D viscous flow calculating method. 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 and a multi-grid acceleration technique was employed to effectively reduce the computational effort and simple zero-equation turbulence model was adopted to closure the Reynolds-averaged Navier-Stokes equations. The mixing plane method and personal computer network parallel computational technique were employed to transfer parameters between rotor and stator cascades. The overall performance of a five-blade-row(Inlet Guide Vane-Zero Stage-One Stage) compressor were simulated and the results were thoroughly analyzed. In order to investigate the influence of the entire multi-blade-row environment to the single stage aerodynamic performance, the overall performance of the front three-blade-row (Inlet Guide Van-Zero Stage) were simulated and the aerodynamic characteristics were compared with the data extracted from the five-blade-row simulation.