| 超音通流风扇叶栅流场数值模拟 |
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| 引用本文： | 马继华,单鹏.超音通流风扇叶栅流场数值模拟[J].北京航空航天大学学报,1994,20(3):271-279. |
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| 作者姓名： | 马继华 单鹏 |
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| 作者单位： | 北京航空航天大学动力系 |
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| 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。
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| 关 键 词： | 超声速 叶栅 流场 航空发动机 |
NUMERICAL SIMULATION OF SUPERSONIC THROUGH-FLOW FAN CASCADE FLOWFIELD |
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| Ma Jihua ,Shan Peng,Zhou Sheng.NUMERICAL SIMULATION OF SUPERSONIC THROUGH-FLOW FAN CASCADE FLOWFIELD[J].Journal of Beijing University of Aeronautics and Astronautics,1994,20(3):271-279. |
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| Authors: | Ma Jihua Shan Peng Zhou Sheng |
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| Institution: | Beijing University of Aeronautics and Astronautics. Dept. of Jet Propulsion |
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| Abstract: | 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. |
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| Keywords: | supersonic cascade flow fields: numerical simulation: supersonic throughflow fan |
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