本文引用格式:揭晓博,张伟.航空发动机叶片非线性振动分析[J].动力学与控制学报,2019,17(3):205~212;   Jie Xiaobo,Zhang Wei.Nonlinear vibration analysis of the aero engine blade[J].Journal of Dynamics and Control,2019,17(3):205-212. 航空发动机叶片非线性振动分析    点此下载全文 北京工业大学 机电学院, 北京 100022 基金项目：国家自然科学基金资助项目(11290152,11427801) DOI：10.6052/1672-6553-2018-068 摘要： 论文研究了航空发动机叶片的非线性振动问题,将叶片简化为旋转圆锥壳,考虑预安装角和预扭转角的影响,利用Hamilton原理建立了不同激励作用下的叶片的非线性偏微分运动方程．综合运用Galerkin方法和数值方法,对叶片进行了非线性动力学分析,模拟不同转速和激励作用下的叶片运动,得到波形图,讨论了转速和外载荷对旋转叶片非线性动力学特性的影响. 关键词：旋转叶片,非线性动力学,圆锥壳,Hamilton原理,Galerkin方法 Nonlinear vibration analysis of the aero engine blade    Download Fulltext Fund Project: Abstract: The nonlinear vibration responses of the aero engine blade were investigated. Considering the effects of the presetting and pre twisted angles, the blade was modeled as a rotating conical shell . Using Hamilton′s principle, the governing partial differential equations of motion under different excitations were established. Both Galerkin′s approach and numerical method were applied to analyze the nonlinear dynamics of the blade. Numerical simulations were performed to investigate the responses of the blade under different rotating speeds and excitations. The results show that both the rotating speed and excitation have effects on the nonlinear dynamics of the blade. Keywords:rotating blade,nonlinear dynamics,conical shell,Hamilton′s principle,Galerkin′s method 查看全文  查看/发表评论  下载PDF阅读器

 您是第3468354位访问者 版权所有:《动力学与控制学报》 地址：湖南省长沙市湖南大学逸夫楼203室　邮编：410082 E_mail: dlxykzxb@hnu.edu.cn 　电话：0731-88822722 本系统由北京勤云科技发展有限公司设计