摘要
由于航空发动机机匣的不连续性,机匣的力学传递特性将受到影响。对传统静子机匣部件振动特性进行分析时,常不考虑机匣螺栓连接结构的影响,从而导致仿真计算的结果产生较大的偏差。基于国内外研究现状,建立螺栓连接结构的有限元分析模型,在力学传递特性方面研究了螺栓预紧力、螺栓分布和螺栓数量对机匣抗弯刚度和振动频率的影响。结果表明:航空发动机机匣螺栓连接结构会导致其结构刚度下降;螺栓预紧力、螺栓分布和螺栓数量是影响航空发动机机匣抗弯刚度和振动频率的主要因素。
Since the aircraft engine casing is a non-continuous structure, which will affect the aircraft engine casing vibration characteristics. In the study of the vibration characteristics of the conventional stator box components, the bolt connection structure of the casing installation side is often neglected, resulting in a large deviation in the vibration simulation results. In this study, the finite element analysis model of bolted connection structure is established based on the finite element method. The influence of bolt preload, bolt distribution and bolt number on the bending stiffness and vibration frequency of the casing is studied. The results show that, due to the presence of the bolted connection structure, the structural rigidity of the casing is reduced. The bolt pretension, distribution and the number of bolts are the main factors that affect the bending stiffness and vibration frequency of an aero-engine case.
出处
《机械科学与技术》
CSCD
北大核心
2017年第12期1964-1969,共6页
Mechanical Science and Technology for Aerospace Engineering
基金
国家重点基础研究发展计划项目(2011cb610505)
国家自然科学基金项目(61240038)资助
关键词
力学特性
接触刚度
螺栓连接结构
振动分析
mechanical properties
contact stiffness
bolt connection structure
vibration analysis
