航空发动机叶片-机匣碰摩热-结构耦合仿真  

Simulation of thermal-structural coupling field during aero-engine blade-to-case rub-impact

作　　者：王丽丽[1] 李舜酩[2] 赖少将[2] 闻静[2] 

机构地区：[1]中国电子科技集团第43所,合肥230088 [2]南京航空航天大学能源与动力学院,南京210016

出　　处：《应用力学学报》2016年第6期1045-1050,1122,共6页Chinese Journal of Applied Mechanics

基　　金：中央高校基础研究基金(XZA15003);机械结构强度与振动国家重点实验室开放课题(SV2015-KF-01)

摘　　要：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。In reaction to the frictional thermal effect during blade-to-case rub-impact, a thermal-structural coupling finite element model is established. The frictional thermal response characteristic of blade-to-case is analyzed by using the thermal-structural coupling element. The distributions of temperature field and equivalent stress field are obtained on the basis of a certain centrifugal force, friction coefficient and rotate speed of the blade. Compared with the stress distribution under solely mechanical load, the diffusion rules of rub-impact thermal response on the blade and case are figured out. It shows that the total stress level increased and generated the thermal deformation in consideration of the thermal stress effect which leads to the deterioration of rub-impact fault. In practice, it is suggested that the rub-impact thermal effect in the process of aero-engine vibration analysis should not be ignored.

关 键 词：叶片-机匣碰摩 摩擦热 热-结构耦合 有限元法 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]