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针对转静子碰摩过程中的摩擦热效应现象,建立了叶片-机匣的碰摩热-结构耦合模型。采用热-结构耦合单元,对航空发动机叶片-机匣进行了碰摩热效应特性研究。考虑摩擦因数及旋转过程中的离心力作用,对瞬态-热结构耦合场进行了有限元分析,研究了结构在温度场作用下的热-结构耦合应力和温度分布。与纯机械载荷下的应力分布对比,发现了碰摩热效应在叶片与机匣上的扩散规律。研究结果表明,考虑摩擦热效应时由于热应力的作用,导致结构的总应力水平升高进而产生热变形,从而使故障进一步恶化。由此可见,碰摩热效应的影响在实际航空发动机振动分析中不能忽视。
Aiming at the phenomenon of frictional heat effect during the rubbing process, the blade-casing friction-heat-structure coupling model was established. The heat-structure coupling unit was used to study the thermal-friction characteristics of aero-engine blade-receiver. Taking into account the friction factor and the centrifugal force during the rotation, the transient-thermal coupling field is analyzed by finite element method, and the thermo-structural coupling stress and temperature distribution of the structure under temperature field are studied. Contrasting with the stress distribution under purely mechanical load, the rule of rubbing heat effect on the blade and casing was found out. The results show that considering the frictional heat effect, the thermal stress causes the total stress level of the structure to increase, resulting in thermal deformation, which further deteriorates the fault. Thus it can be seen that the impact of frictional heat effects can not be neglected in the actual aeroengine vibration analysis.