| 跨音涡轮叶栅吸力面气膜/激波交互作用的数值研究（英文） |
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| 作者姓名： | 黄康 陈帝云 李世峰 时培杰 马护生 |
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| 作者单位： | Aerospace Technology Institute, China Aerodynamics Research and Development Center |
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| 基金项目： | National Natural Science Foundation of China (51806233)；;National Major Science and Technology Project (2017-Ⅲ-0003-0027)； |
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| 摘 要： | The interaction between the cooling film on the suction surface of the transonic turbine cascade and the shock wave in the passage is analyzed by numerical calculation method. The effects of cooling pressure and incident angle on the shock wave shape and the film cooling efficiency under the action of shock wave are studied. The results show that with the increase of exit Mach number, the incident position of the left shock wave at the trailing edge of the cascade moves backward relative to the ...
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