一种改进的航发螺栓连接薄层单元建模方法  

An Improved Thin Layer Element Method of Aeroengine Bolted Joints

作　　者：许致华[1] 刘丁 洪振宇[1] 张桂昌[1] XU Zhi-hua;LIU Ding;HONG Zhen-yu;ZHANG Gui-chang(Civil aviation university of China,Tianjin 3OO300,China)

机构地区：[1]中国民航大学,天津300300

出　　处：《计算机仿真》2020年第7期100-106,共7页Computer Simulation

基　　金：国家自然科学基金民航联合基金培育项目(U1833108);中央高校基本科研业务费项目中国民航大学专项(3122018C010,3122018D038)。

摘　　要：针对航空发动机螺栓连接结构的特殊性,对航空发动机螺栓连接结构薄层单元建模方法进行研究。给出建模原理,基于ANSYS研究螺栓预紧力大小、螺栓数目或螺栓间距对螺栓连接面的影响,得出螺栓连接面轴向应力的变化规律,进而得出改进的航空发动机螺栓连接结构薄层单元建模方法及材料参数,最后应用到实际结构中,并与精细有限元模型结果作对比,验证方法的正确性。研究表明:改进的薄层单元法可以更好地模拟航空发动机螺栓连接结构,较为准确地反映螺栓预紧力的作用效果。In view of the particularity of the aeroengine bolted connection structure,the thin layer element modeling method of aero-engine bolt connection structure was studied.The modeling principle was given.Based on ANSYS,the influence of bolt preload force,number of bolts or distance between bolts on bolt connection surface was studied,and the variation law of axial stress of bolt connection surface was received,then the improved thin layer element modeling method and material parameters of aero-engine bolted structure were obtained,finally the method was applied to the actual structure,and compared with fine finite element model results,the correctness of the method was verified.The results show that the improved thin layer element method could better simulate the bolt connection structure of aero-engine and accurately reflected the effect of bolt pre-tightening force.

关 键 词：螺栓连接 航空发动机 轴向应力 薄层单元法 

分 类 号：V232.7[航空宇航科学与技术—航空宇航推进理论与工程]