| 叶轮机械颤振稳定性工程预测方法在跨声风扇中的进一步探讨 |
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| 引用本文： | 张正秋,邹正平,王延荣,刘火星.叶轮机械颤振稳定性工程预测方法在跨声风扇中的进一步探讨[J].航空动力学报,2010,25(3):537-548. |
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| 作者姓名： | 张正秋 邹正平 王延荣 刘火星 |
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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科技重点实验室,航空发动机数值仿真研究中心,北京,100191 |
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| 摘 要： | 通过求解雷诺平均Navier-Stokes(N-S)方程并采用影响系数法,对三个基本正交模态的三维振荡跨声风扇叶片绕流问题进行了研究,基于刚体运动假设和模态叠加法,得到了可用于叶轮机械设计阶段颤振稳定性评估的稳定性参数图.结果表明,跨声风扇内部,激波对非定常气动力的分布具有主导作用;在一定情况下振型对颤振稳定性有重要影响,应将其作为颤振稳定性设计的重要参数之一;跨声风扇和亚声低压涡轮的稳定性参数图对比分析表明,两者稳定性参数分布形式具有相似性.
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| 关 键 词： | 颤振 稳定性参数 振荡叶栅 影响系数法 跨声风扇 |
| 收稿时间： | 2009/2/27 0:00:00 |
| 修稿时间： | 8/6/2009 12:00:00 AM |
Investigation of flutter prediction method for transonic fan |
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| ZHANG Zheng-qiu,ZOU Zheng-ping,WANG Yan-rong and LIU Huo-xing.Investigation of flutter prediction method for transonic fan[J].Journal of Aerospace Power,2010,25(3):537-548. |
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| Authors: | ZHANG Zheng-qiu ZOU Zheng-ping WANG Yan-rong and LIU Huo-xing |
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| Affiliation: | Aeroengine Numerical Simulation Research Center, National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;Aeroengine Numerical Simulation Research Center, National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;Aeroengine Numerical Simulation Research Center, National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;Aeroengine Numerical Simulation Research Center, National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China |
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| Abstract: | Numerical simulation of three-dimensional unsteady viscous flow around oscillating transonic fan was carried out in the influence coefficient domain with one blade oscillating in various three-dimensional rigid-body modes.Then the stability parameter map was gotten based on the assumption of rigid body mode and mode superposition method.The main result of this paper is that,the shock wave has dominant contribution on the unsteady aerodynamic force,mode shape has an important effect on flutter stability,and the stability parameter of transonic fan and subsonic low pressure turbine has similar pattern. |
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| Keywords: | flutter stability parameter oscillating cascade influence coefficient method transonic fan |
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