| 超跨声涡轮叶栅尾缘激波系流动研究 |
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| 引用本文： | 周志鸿,刘火星,陈云,王雷. 超跨声涡轮叶栅尾缘激波系流动研究[J]. 工程热物理学报, 2021, 42(1): 73-80 |
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| 作者姓名： | 周志鸿 刘火星 陈云 王雷 |
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| 作者单位： | 北京航空航天大学能源与动力工程学院，航空发动机气动热力国家级重点实验室，北京100191;中国航空发动机集团沈阳发动机研究所,沈阳110015 |
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| 摘 要： | 本文通过分析超跨声涡轮尾缘波系的流动机理给出了详细的尾缘激波系流动图画,强调了尾缘分离激波的重要作用.经过分析,认为基底区压力是通过影响基底区宽度来影响涡轮叶栅尾缘激波强度的.最后将上述机理应用到某叶栅S1计算程序的改进工作中,数值计算和叶栅试验结果表明,改进工作有效提高了该程序对超跨声涡轮叶栅尾缘激波流动的模拟能力.
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| 关 键 词： | 超跨声涡轮 尾缘 激波系 基底区 |
Study on the Trailing Edge Shock Wave System in Ultra-Transonic Turbine Cascade |
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| ZHOU Zhi-Hong,LIU Huo-Xing,CHEN Yun,WANG Lei. Study on the Trailing Edge Shock Wave System in Ultra-Transonic Turbine Cascade[J]. Journal of Engineering Thermophysics, 2021, 42(1): 73-80 |
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| Authors: | ZHOU Zhi-Hong LIU Huo-Xing CHEN Yun WANG Lei |
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| Affiliation: | (National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy and Power Engineering,Beihang University,Beijing 100191,China;AECC Shenyang Engine Research Institute,Shenyang 110015,China) |
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| Abstract: | In this paper,a detailed flow sketch of trailing edge shock wave system is given by analyzing the flow mechanism in ultra-transonic turbine cascade,and the important role of trailing edge separation shock wave is emphasized.It is concluded that the base pressure influences the trailing edge shock wave intensity in the turbine cascade by affecting the width of the base region.Finally,the above mechanism is applied to the improvement of a cascade S1 calculation program.The numerical calculation and cascade test results show that the program simulation ability of the trailing edge shock wave system in ultra-transonic turbine cascade has been effectively improved. |
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| Keywords: | ultra-transonic turbine trailing edge shock wave system base region |
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