航空发动机内外涵道三维粘性流场的数值模拟  

3-D VISCOUS NUMERICAL SIMULATION OF FAN-BYPASS-COMPRESSOR

作　　者：赵永辉[1,2] 张宏武[1] 聂超群[1] 黄伟光[1] 

机构地区：[1]中国科学院工程热物理研究所 [2]中国科学院研究生院,北京100080

出　　处：《工程热物理学报》2005年第5期758-760,共3页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.50276059)

摘　　要：本文用数值模拟的方法,对某涡扇发动机从风扇入口到增压级出口以及整个外涵道的稳态流场进行了联算和分析,计算是在我们自主搭建的分布式平行网络平台上进行的。计算表明风扇叶片沿叶高马赫数变化较大,从叶根附近的0.56变化到叶顶的1.34。本文得出了比较详细的内外涵道流场的信息,为叶片优化设计以及气动声学评估提供了依据。Numerical methods were utilized to analyze steady flow field in a fan-bypass-core compressor configuration. The calculation was run on a distributed parallel network platform which was constructed by ourselves. The simulation results showed that the relative Mach number varied a lot along the blade span at the fan inlet from 0.56 near the hub to 1.34 at the tip. The detail flow field information provided by the calculation can be used as a reference for blade optimal design and aerodynamic and acoustic performance evaluation of the engine.

关 键 词：涵道 涡扇发动机 数值模拟 

分 类 号：TK474[动力工程及工程热物理—动力机械及工程]