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安装边泄漏对航空发动机的工作效率影响较大,现有文献关于发动机安装边泄漏特性的研究较少。基于断裂力学理论,推导了法兰安装边泄漏压力与安装边应力关系公式,建立了某型航空发动机安装边三维有限元模型,研究了安装边厚度、螺栓数量、螺栓直径以及螺栓预紧力对安装边泄漏压力的影响。研究表明:安装边的泄漏压力随着螺栓数量以及预紧力的增加而增大,随着安装边厚度的增加而减小,随着螺栓直径的增加先增大后减小。研究为航空发动机机匣安装边结构参数设计提供了参考。
The leakage of the installation side has a great influence on the working efficiency of the aeroengine. There are few studies on the leakage characteristics of the engine mounting side in the existing literature. Based on the theory of fracture mechanics, the formula of the relationship between flange side leakage pressure and installation side stress is deduced, and the three-dimensional finite element model of a certain type of aero-engine mounting side is established. The influences of the installation side thickness, bolt number, bolt diameter and bolt pre- Impact of installation side leakage pressure. The research shows that the leakage pressure of the mounting side increases with the increase of the bolt number and the pretightening force, decreases with the increase of the thickness of the mounting side, and then increases with the increase of the diameter of the bolt first and then decreases. The research provides a reference for the design of aeroengine casing mounting side structure parameters.