跨声速轴流压气机级全工况三维流场数值分析  

3-D viscous numerical investigation on the overall aerodynamic performance of a transonic axial-flow compressor stage

作　　者：张士杰[1] 袁新[2] 叶大均[2] 

机构地区：[1]清华大学建筑学院,北京100084 [2]清华大学热能工程系,北京100084

出　　处：《推进技术》2002年第3期209-212,共4页Journal of Propulsion Technology

基　　金：国家重点基础研究专项经费 (G19990 2 2 30 4 );国家自然科学基金 (5 0 0 76 0 19)资助项目

摘　　要：以LU SGS GE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 ,对三维可压缩雷诺平均N S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。计算得到了NASA 35号低展弦比、跨声速轴流压气机级 70 %和 90 %设计转速下的全工况性能曲线 ,并重点分析了其中一些典型工况下的内部流场。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 。The internal flow field of a transonic axial flow compressor stage 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 was employed to effectively reduce the computational effort and simple zero equation turbulence model was adopted to closure the Reynolds averaged N S equations The mixing plane method was employed to transfer parameters between rotor and stator cascades The overall performance for a compressor stage at different rotating speed was obtained and the internal flow fields at typical operating conditions were emphatically analyzed Compared with the results obtained from experimental data, these solutions demonstrate both the efficiency and accuracy needed by practical applications

关 键 词：跨音速压气机 三维流动 气动特性 数值计算 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程]