亚声速气流激励下旋转叶片的饱和渗透现象

刘艮; 陈贡发; 袭安

doi:10.13224/j.cnki.jasp.2020.05.002

亚声速气流激励下旋转叶片的饱和渗透现象

doi: 10.13224/j.cnki.jasp.2020.05.002

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出版历程
- 收稿日期: 2019-12-06
- 刊出日期: 2020-05-28

Subsonic airflow load of rotating blades excited by subsonic flow

1.
School of Civil and Transportation Engineering,Guangdong University of Technology,Guangzhou 510006,China
2.
The Fifth Electronic Research Institute,Ministry of Industry and Information Technology of the People’s Republish of China,Guangzhou 510610,China

摘要

摘要: 研究了在1∶2内共振条件下,压气机叶片在亚声速气流作用下的非线性耦合振动响应。利用涡格法得到了三维绕流压气机叶片的横向气动载荷。采用Chebyshev-Ritz法获得旋转叶片的第一阶扭转模态和第二阶弯曲模态的模态函数,并将计算出的前三阶频率并与有限元计算结果进行对比。利用Galerkin法对系统的偏微分方程进行截断,得到扭转模态与弯曲模态的两自由度常微分方程。通过对存在线性刚度项耦合的系统进行了求解,得到了系统存在的两种可能的解支,并对其进行稳定分析。通过对系统两阶模态间能量传递的分析,计算了当调谐参数为σ=0,σ1≠0以及调谐参数为σ=0,σ1=0时系统扭转模态与弯曲模态的力-幅曲线,分析了模态幅值间的饱和行为和能量传递的现象,当外激励调谐参数σ1=0时,扭转模态幅值的跳跃现象消失。同时分析了不同参数对力-频、幅-频特性的影响。
- 亚声速气流 /
- 压气机叶片 /
- 非线性耦合振动 /
- 能量传递 /
- 饱和跳跃现象
Abstract: The nonlinear coupled vibration response of the compressor blade under subsonic flow and the condition of 1∶2 internal resonance was studied. The transverse aerodynamic loads of three-dimensional compressor blades were obtained by the vortex lattice method (VL). The mode functions of the first torsional mode and the second bending mode of the rotating blade were obtained by the Chebyshev-Ritz method and the first three frequencies were compared with the finite element results. By using Galerkin method, the partial differential equations of the system were truncated, and the two-degree-of-freedom ordinary differential equations of the torsional mode and the bending mode were obtained. By solving the equations with linear coupling stiffness term, two possible solutions were obtained and the stability analysis was investigated. Through analysis of the energy transfer between these two modes of the system, the force amplitude curve of the torsional mode and the bending mode of the system was calculated when the tuning parameter was σ=0, σ1≠0 and the tuning parameter was σ=0, σ1=0. The saturation behavior and the phenomenon of energy transfer between the modal amplitudes were analyzed. When the external excitation tuning parameter was σ1=0, the jump phenomenon of the torsional mode amplitude disappeared. At the same time, the influences of different parameters on force frequency and amplitude frequency characteristics were analyzed.
- subsonic airflow load /
- compressor blade /
- nonlinear coupled vibration /
- energy transfer /
- saturation and jumping phenomena

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