Abstract: 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[Fp] was small，the dimensionless bolted joint stiffness[K] increased slowly with the increase of bolt preload[Fp]. When [Fp]reaching to 27.5kN，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].

Key words: Aero-engine；Bolted joints stiffness；Half-apex angle；Stress distribution；Bolt stiffness；Member stiffness

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[Fp]较小时，无量纲连接刚度[K]随着螺栓预紧力[Fp]的增加缓慢增加，当预紧力[Fp]增加到27.5kN时，双层的无量纲连接刚度[K]为27，且趋于稳定；并且[n]，[Fp]对无量纲连接刚度[K]的影响还与锥形半角[α]有关。

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