等离子体合成射流主动控制平面叶栅叶片流致振动

doi:10.7527/S1000-6893.2023.28430

Abstract

Abstract:

The tip gap leakage vortex of the compressor rotor blade is an important cause of its vibration failure. To suppress the blade vibration intensity induced by tip clearance leakage vortex， 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. Then， the plasma synthesis jet is used to actively control the leakage vortex between blade tips and suppress the vibration caused by the blade. The control effects of different jet layouts and excitation frequencies are explored， and the control mechanism is clarified. The results show that when the incoming flow velocity is 30 m/s and the blade installation angle is 15°， blade resonance occurs. The interstitial leakage vortex of the tip gap flows 0.25 and 0.50 times the chord length cross-section， which is the key position for active control of the plasma synthesis jet. At 0.50 times the chord length cross-section， plasma synthetic jets sprayed in the direction of the blade basin control vibration best compared to the 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 leakage flow between the blade tip， reduces the pressure gradient of the blade pressure surface and the suction surface， 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: compressor, rotor blade, flow-induced vibration, plasma synthetic jet, tip leakage vortex, particle image velocimetry

CLC Number:

V211

Rubing LIU, Zefan CHEN, Ruixin LIN, Qi LIN. Active control of flow-induced vibration of blades in a plane cascade by a plasma synthetic jet[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(20): 128430-128430.

Figures/Tables 24

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参数	数值
弦长c/mm	40
叶高h/mm	195
叶厚λ/mm	1
叶尖间隙δ/mm	5
栅距s/mm	30
安装角γ/（°）	15
叶尖间隙比τ/%	2.6

激励器参数	数值
腔体外径D/mm	6
腔体长度L/mm	40
射流孔长度l/mm	40
射流孔内径d/mm	2
电极间距∆/mm	10

阶数	仿真结果/Hz	试验结果/Hz
1	73.7	39.0
2	160.0	156.5
3	485.6	478.3
4	563.0	527.0

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Active control of flow-induced vibration of blades in a plane cascade by a plasma synthetic jet

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频率/Hz	占空比/%	加载电压/kV	射流能量Q_d/mJ
100	10	20	0.58
200	10	20	0.43
220	10	20	0.33
240	10	20	0.21
300	10	20	0.12