| 跨声速压气机转子叶尖流场旋转不稳定现象的数值研究 |
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| 引用本文： | 付磊,袁巍,宋西镇,周盛,陆利蓬.跨声速压气机转子叶尖流场旋转不稳定现象的数值研究[J].航空动力学报,2014,29(5):1145-1153. |
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| 作者姓名： | 付磊 袁巍 宋西镇 周盛 陆利蓬 |
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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;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;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;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;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 |
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| 基金项目： | 国家自然科学基金（50906001） |
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| 摘 要： | 对某跨声速压气机转子在不同工作流量下的叶尖非定常流场进行了数值研究.结果显示:大流量状态下,该转子叶尖流场几乎不发生振荡.此时,叶尖流场可以按定常流场进行分析;小流量状态下,叶尖泄漏涡大幅振荡,相邻叶片通道内的叶尖泄漏流之间也存在周期性相互干涉.其结果是在稳定状态时出现由于叶尖泄漏涡的振荡及其周向传播造成的"旋转不稳定"现象."旋转不稳定"流场结构主模态旋涡个数大约为40%的叶片通道个数;其周向尺度占据2~3个栅距.
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| 关 键 词： | 跨声速压气机转子 旋转不稳定 叶尖泄漏流 非定常流动 模态分析 |
| 收稿时间： | 2013/11/29 0:00:00 |
Numerical investigation on rotating instability phenomenon in tip flow field of transonic compressor rotor |
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| FU Lei,YUAN Wei,SONG Xi-zhen,ZHOU Sheng and LU Li-peng.Numerical investigation on rotating instability phenomenon in tip flow field of transonic compressor rotor[J].Journal of Aerospace Power,2014,29(5):1145-1153. |
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| Authors: | FU Lei YUAN Wei SONG Xi-zhen ZHOU Sheng and LU Li-peng |
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| Institution: | National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China |
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| Abstract: | Numerical simulations were performed on tip unsteady flow field of a transonic compressor rotor with different work mass flows. The results show that no oscillation occurs in tip flow field of rotor under high mass flow condition, which can be regarded as steady flow field for analysis, and the oscillation of tip leakage vortex is intensive under low mass flow conditions. Furthermore, periodical interference within the tip leakage flow between adjacent blade passages emerges. As a result, a phenomenon called "rotating instability" caused by the oscillation of tip leakage vortices and its circumferential propagation, is found in stationary frame. The dominating cell number of "rotating instability" flow field is nearly 40% of the blade passage number, and the cell size in circumferential direction is 2-3 pitches. |
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| Keywords: | transonic compressor rotor rotating instability tip leakage flow unsteady flow modal analysis |
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