NASA67跨音风扇级内粘性流场的准定常数值模拟  

NUMERICAL QUASI-STEADY STUDY ON THE INTERNAL VISCOUS FLOW IN NASA67 TRANSONIC FAN STAGE

作　　者：赖焕新[1] 康顺[1] 

机构地区：[1]中国科学院工程热物理研究所,北京100080

出　　处：《工程热物理学报》2000年第3期302-305,共4页Journal of Engineering Thermophysics

基　　金：国家自然科学基金!No.59876042

摘　　要：本文使用商业软件数值研究ＮＡＳＡ６７跨音速两级风扇第一级在近最高效率点和近堵塞工况点的三维粘性流场。对用细网格计算的级内流场进行了细致的分析，揭示了转子中的激波、附面层、间隙涡、分离流动、流动径向掺混等流动现象，给出了转子与静子叶道中的二次流动和能量损失的分布。The three dimensional viscous flows in the first stage of NASA67 transonic fan, at near peak efficiency point and near stall point, are investigated numerically employing a commercial software named as FINE/TURBO. Detailed analysis are processed for the computational results with fine mesh employed. The phenomena such as shock/boundary layer interaction, blade tip-clearance leakage vortex, flow separation and radial mixing, are revealed, and the results of secondary flow and energy loss distribution in the flow passages are also can be found in this paper.

关 键 词：跨音速风扇 粘性流动场 数值模拟 

分 类 号：O357[理学—流体力学]