| 上游尾迹与涡轮叶栅通道涡相互作用研究 |
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| 引用本文： | 綦蕾,郑贇,邹正平,刘火星,李维,周颖,许如琦.上游尾迹与涡轮叶栅通道涡相互作用研究[J].航空动力学报,2008,23(5):895-903. |
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| 作者姓名： | 綦蕾 郑贇 邹正平 刘火星 李维 周颖 许如琦 |
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| 作者单位： | 1. 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重点实验室,航空发动机数值仿真研究中心,北京,100083
2. 中国航空动力机械研究所,株洲,412002 |
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| 基金项目： | 国家自然科学基金
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国防科技应用基础研究基金
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北京航空航天大学蓝天新星计划 |
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| 摘 要： | 采用三维粘性非定常数值模拟方法研究了上游尾迹与涡轮叶栅通道涡的相互作用,对定常、非定常时均以及瞬时时刻流动机理进行了分析.结果表明:上游尾迹的非定常作用一方面增强了叶栅通道涡的径向涡,使得流动损失增大;另一方面能够一定程度上抑制通道涡中流向涡的发展,对控制损失起到正面作用,端区的综合非定常效应取决于两者之间的平衡.在本文计算条件下,上述两方面综合影响使得通道涡的非定常损失增大.
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| 关 键 词： | 航空、航天推进系统 通道涡 上游尾迹 非定常相互作用 涡轮叶栅 |
| 文章编号： | 1000-8055(2008)05-0895-09 |
| 收稿时间： | 2007/4/20 0:00:00 |
| 修稿时间： | 2007年4月20日 |
Upstream wake-passage vortex interaction in turbine cascade |
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| QI Lei,ZHENG Yun,ZOU Zheng-ping,LIU Huo-xing,LI Wei,ZHOU Ying and XU Ru-qi.Upstream wake-passage vortex interaction in turbine cascade[J].Journal of Aerospace Power,2008,23(5):895-903. |
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| Authors: | QI Lei ZHENG Yun ZOU Zheng-ping LIU Huo-xing LI Wei ZHOU Ying and XU Ru-qi |
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| Institution: | Aeroengine Numerical Simulation Research Center, National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;Aeroengine Numerical Simulation Research Center, National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;Aeroengine Numerical Simulation Research Center, National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;Aeroengine Numerical Simulation Research Center, National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;China Aviation Powerplant Research Institute, Zhuzhou 412002, China;China Aviation Powerplant Research Institute, Zhuzhou 412002, China;China Aviation Powerplant Research Institute, Zhuzhou 412002, China |
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| Abstract: | The internal flow of turbomachinery is intrinsically unsteady,so investigating the unsteady interactions in turbine endwall region is meaningful for improving the performance of low aspect/high loading turbine.In this paper,the upstream wake-passage vortex interactions in turbine cascade were simulated by a 3-D unsteady viscous solver,and the flow mechanisms were analyzed.Numerical results indicate that periodic upstream wakes can enhance the radial vorticity of passage vortex,which increases losses.On the other hand,upstream wakes can suppress the streamwise vorticity development of passage vortex to some extent,which reduces losses.The combined unsteady effect in the endwall region depends on the balance of above two factors.At the calculation conditions of this paper,the unsteady losses finally increased. |
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| Keywords: | aerospace propulsion system passage vortex upstream wake unsteady interaction turbine cascade |
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