转动盘一片系的循环对称模综  

CYCLO-SYMMETRIC MODAL SYNTHESIS OF ROTATING BLADED DISC SYSTEM

作　　者：张锦[1] 陈向均 王文亮[3] 

机构地区：[1]北京航空航天大学,100083 [2]航空发动机设计研究所,无锡214063 [3]复旦大学,上海200433

出　　处：《固体力学学报》1992年第3期225-234,共10页Chinese Journal of Solid Mechanics

摘　　要：本文考察在任意恒定转速下叶片/轮盘系的固有模态分析,计及叶片预扭所引起的大变形效应.把群论算法用于子结构技术,通过联立迭代求出叶片/轮盘系在离心场中的平衡位置和应力分布,进而确定初应力刚度矩阵、大变形刚度矩阵,以及相应的动频模态.由于本方法考虑了叶片大变形的影响,且可消去子结构间的全体内连自由度。从而在确保精度的前提下,显著地压缩了计算的规模.实践证明本文提出的子结构联立迭代法有很好的收敛性,它使计算量有巨大的节省.The natural mode analysis of bladed disc system at an arbitrary constant rotational speed is investi-gated in this paper and the large deformation effect caused by the pretorsion of the blades is also consid-ered.The computational method of group theory is employed in substructure technique and the equilib-rium position and stress distribution of the bladed disc system in centrifugal field are obtained throughsimultaneous iteration,further more,the initial stress stiffness matrix,the large deformation stiffness ma-trix and the corresponding rotating natural frequencies and modal shapes are determined:Because thelarge deformation effect of the blades is considered and all the interface degrees of freedom between thesubstructures can be eliminated in the present method,the computation work can be cut down remarka-bly under the precondition of that the computational accuracy is ensured.It shows practically that thesubstructure simultaneous iteration method presented in this paper has a good convergency and greatlyreduces the computation work.

关 键 词：模态综合 航空发动机 叶片 轮盘 

分 类 号：V232[航空宇航科学与技术—航空宇航推进理论与工程]