摘要
用矢通量分裂法求解Ｎ－Ｓ方程和Ｅｕｌｅｒ方程，对超音通流风扇叶栅流场进行了数值模拟．由计算结果给出的物理图象表明：叶栅通道内没有强激波，亦未出现分离回流，全叶栅流场均为超音速，说明计算的两种叶型符合设计要求，其性能有待实验检验．
The numerical simulation of supersonic through-flow fan cascade flow field was conducted by using Flux Vector Splitting in solving N-S equations and Euler equations. The physicalpictures of the compUtational results show that there are neither strong shock nor separationand reversed flow in the cascade passage. The whole cascade flow field is proved to be the supersonic flow. Which is an indication that the calculated two cascade flow fields satisfy thedesign requirement. The performance still needs to be examined in the future experiments.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
1994年第3期271-279,共9页
Journal of Beijing University of Aeronautics and Astronautics
关键词
超声速
叶栅
流场
航空发动机
supersonic cascade
flow fields: numerical simulation: supersonic throughflow fan
