航空发动机螺栓连接载荷与结构参数对连接刚度影响规律  

Effects of Load and Structure Parameters of Aero-Engine Bolted Joints on Joint Stiffness

作　　者：姚星宇[1] 王建军[1] YAO Xing-yu WANG Jian-jun(Schoolof Energy and Power Engineering, Beihang University, Beijing 100191, China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《推进技术》2017年第2期424-433,共10页Journal of Propulsion Technology

摘　　要：从航空发动机复杂螺栓连接结构的特殊性出发,根据不同连接形式的螺栓连接结构轴向应力分布,提出了航空发动机复杂螺栓连接结构的连接刚度理论表达式,并进一步研究了航空发动机螺栓连接载荷、结构参数对连接刚度的影响规律。研究结果表明:当螺栓个数n在4~30之间变化时,双层的无量纲连接刚度K在8.9~66.8之间线性的变化;当螺栓预紧力F_p较小时,无量纲连接刚度K随着螺栓预紧力F_p的增加缓慢增加,当预紧力F_p增加到27.5k N时,双层的无量纲连接刚度K为27,且趋于稳定;并且n,F_p对无量纲连接刚度K的影响还与锥形半角α有关。Based on the particularity of aero-engine bolted joints and the axial stress distribution of bolted joints of different styles,the stiffness theory of aero-engine bolted joints was proposed,and the effects of load and structure parameters on the joint stiffness were further studied. The results indicated that when the bolt numbers n changed between 4 and 30,the dimensionless bolted joint stiffness K of double members varied linearly between 8.9 and 66.8. When the bolt preload Fpwas small,the dimensionless bolted joint stiffness K increased slowly with the increase of bolt preload Fp. When Fpreaching to 27.5k N,the dimensionless bolted joint stiffness K of double members was 27 and tended to be stable; and the effects of n,Fp on the dimensionless bolted joint stiffness K were also concerned with half-apex angle α.

关 键 词：航空发动机 螺栓连接刚度 锥形半角 应力分布 螺杆刚度 法兰边刚度 

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]