摘要
发展了一种理论方法的计算程序 ,研究耦合转子 /机舱 /塔架系统气弹响应问题。利用以 Hamilton原理为基础的有限元法 ,应用 5节点 18自由度和 2节点 12自由度的梁单元模型分别离散桨叶和塔架。机舱简化为刚体 ,具有刚体一般运动。风模型为 2维拟定常风。采用子空间迭代法求解桨叶、机舱和塔架动力学方程。其中 ,桨叶非线性动力学方程具有周期时变系数 ,求解采用拟线性法。计算结果表明 :工作转速下风机能够安全、稳定运转。转子转速远远高于工作转速时 。
The aeroelastic response of a coupled rotor/nacelle/tower system was analyzed using the finite element method based on Hamilton's principle. 5 node 18 degree of freedom and 2 node 12 degree of freedom beam elements were developed for the discretization of the blades and tower, respectively. The nacelle was simplified to a rigid body with general motion. The 2 D quasi steady wind model was established. The dynamical equations for the blades, the nacelle and the tower including the aeroelastic response were solved using the dynamical substructure method. The nonlinear dynamical equation for the rotor blades with time dependent periodic coefficients was evaluated using a modified quasi linearization method. The results show that the system is stable and safe at the working rotational velocity. The system motion will be unstable only when the rotational velocity is much quicker than the working velocity.
出处
《清华大学学报（自然科学版）》
EI
CAS
CSCD
北大核心
2002年第2期211-215,共5页
Journal of Tsinghua University(Science and Technology)
基金
国家"九五"科技攻关项目 ( 96 -A17-0 1-0 1-0 2 )
