等离子体合成射流主动控制平面叶栅叶片流致振动的实验研究

doi:10.7527/S1000-6893.2023.28430

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等离子体合成射流主动控制平面叶栅叶片流致振动的实验研究

刘汝兵¹,陈泽帆¹,林瑞鑫¹,林麒²

1. 厦门大学航空航天学院
2. 福建省厦门市厦门大学航空系

收稿日期:2022-12-26 修回日期:2023-02-28 出版日期:2023-03-03 发布日期:2023-03-03
通讯作者: 刘汝兵
基金资助:
国家自然科学基金;中国航空发动机集团产学研合作项目;航空动力基金项目;中央高校基本科研业务费专项资金

Experimental study on active control of flow-induced vibration of planar blade blades of compressor plane blades by plasma synthetic jet

Received:2022-12-26 Revised:2023-02-28 Online:2023-03-03 Published:2023-03-03
Contact: Ru-Bing LIU

摘要/Abstract

摘要： 压气机转子叶片的叶尖间隙泄漏涡是造成其振动故障的重要诱因。通过平面叶栅风洞试验，捕捉叶片振动现象，分析振动模态特征，测量叶尖间隙涡的流动结构。进而，利用等离子体合成射流主动控制叶尖间隙泄漏涡，抑制叶片流致振动强度。并探究了不同射流布局和激励频率的控制效果，厘清了控制机理。研究结果表明来流速度为30 m/s，叶片安装角为15°时，叶片发生了共振。叶尖间隙泄漏涡沿流向0.25及0.5倍弦长横截面为等离子体合成射流主动控制关键位置。在0.5倍弦长截面，相较于朝叶尖端面和叶背喷射，朝叶盆方向喷射的等离子体合成射流控制振动的效果最佳。在激励频率220 Hz时，减小叶片振动应力达31.6 %。其控制机理是等离子体合成射流干预了叶尖间隙泄漏流的启动，减小了叶片压力面和吸力面的压力梯度，抑制了叶尖泄漏涡的形成和发展，从而降低了泄漏涡的强度，减小了诱发叶片振动的激振力。

关键词: 压气机, 转子叶片, 流致振动, 等离子体合成射流, 叶尖间隙泄漏涡, PIV

Abstract: The tip gap leakage vortex of the compressor rotor blade is an important cause of its vibration failure. Through the planar blade grid wind tunnel test, the blade vibration phenomenon is captured, the vibration mode characteristics are analyzed, and the flow structure of the blade tip gap vortex is measured. Furthermore, plasma synthesis jet is used to actively control the leakage vortex between the blade tips and suppress the vibration intensity caused by the blade. The control effects of different jet layouts and excitation frequencies were explored, and the control mecha-nism was clarified. The results show that when the incoming flow velocity is 30 m/s and the blade installation angle is 15°, the blade resonance. The interstitial leakage vortex of the tip gap flows 0.25 and 0.5 times the chord length cross-section, which is the key position of the plasma synthesis jet active control. At 0.5 times the chord length cross-section, plasma synthetic jets sprayed in the direction of the blade basin control vibration best compared to spraying towards the tip and back of the leaf. At the excitation frequency of 220 Hz, the vibration stress of the blade is reduced by 31.6%. The control mechanism is that the plasma synthesis jet intervenes in the initiation of the leak-age flow between the blade tip, reduces the pressure gradient of the blade pressure surface and the suction sur-face, inhibits the formation and development of the tip leakage vortex, thereby reducing the strength of the leakage vortex and reducing the excitation force that induces blade vibration.

Key words: Compressors, Rotor blades, Flow-induced vibration, Plasma synthesis jet, Tip leakage vortex, PIV

中图分类号:

V211

刘汝兵陈泽帆林瑞鑫林麒. 等离子体合成射流主动控制平面叶栅叶片流致振动的实验研究[J]. 航空学报, doi: 10.7527/S1000-6893.2023.28430.

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等离子体合成射流主动控制平面叶栅叶片流致振动的实验研究

Experimental study on active control of flow-induced vibration of planar blade blades of compressor plane blades by plasma synthetic jet

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