摘要
针对旋转叶片的气动弹性问题,将带叶冠的叶片简化为末端加质量块的均质悬臂梁。悬臂梁受到离心力和气动力作用,发生弯曲和扭转耦合振动变形。利用Hamilton原理建立了叶片的偏微分运动方程。对方程无量纲化,运用Galerkin方法对其离散,得到两自由度的非线性常微分方程。通过数值求解叶片颤振速度和极限环响应,并用谐波平衡法求解极限环响应与数值解进行对比。最后,讨论了结构参数对颤振速度和极限环响应幅值的影响。
In order to deal with the aerodynamic elasticity of rotating blades,a shrouded blade was simplified as a homogeneous cantilever beam with end mass.The cantilever beam was subjected to centrifugal force and aerodynamic force,and coupled bending and torsion vibration occured.The partial differential motion equation of the blade was established by using the Hamiltonian principle.After making the equation dimensionless,nonlinear ordinary differential equations with two degrees of freedom were obtained by using the Galerkin method.The flutter velocity and limit cycle oscillation response of the blade were solved by numerical method.The harmonic balance method was utilized to analyze the limit cycle oscillation responses,and the results were compared with the numerical solutions.The influences of structural parameters on the flutter velocity and limit cycle oscillation amplitudes were discussed.
作者
麻岳敏
曹树谦
郭虎伦
MA Yuemin;CAO Shuqian;GUO Hulun(Department of Mechanics,Tianjin University,Tianjin 300354,China;Tianjin Key Laboratory of Nonlinear Dynamics and Control,Tianjin 300354,China;National Demonstration Center for Experimental Mechanics Education,Tianjin University,Tianjin 300354,China)
出处
《振动与冲击》
EI
CSCD
北大核心
2019年第2期67-74,共8页
Journal of Vibration and Shock
基金
国家重点基础研究发展计划资助(2015CB057400)
国家自然科学基金(11302145
11672201)
关键词
旋转带冠叶片
耦合颤振
弯扭变形
极限环(LCO)
rotating shrouded blade
coupled flutter
bend and torsion deformation
limit cycle oscillation(LCO)