某型弹用涡扇发动机振动故障建模与分析  

Failure Modeling and Analysis of a Missile Turbofan Engine

作　　者：王海飞[1] 陈果[1] 廖仲坤 张璋[2] 

机构地区：[1]南京航空航天大学民航学院,南京210016 [2]北京动力机械研究所,北京100074

出　　处：《航空发动机》2015年第2期66-70,共5页Aeroengine

基　　金：国家安全重大基础研究项目(613139);国家自然科学基金(61179057)资助

摘　　要：针对某型弹用涡扇发动机振动超标问题,建立了1维有限元梁模型进行仿真与模拟,并结合实际试车数据进行了故障分析和仿真。结果表明:压气机前、后支承刚度对系统第2阶临界转速有很大影响,不合适的支承刚度使系统在工作转速范围内出现第2阶临界转速,从而导致整机振动超标。因此,降低该故障的途径是有效控制支承装配精度。Aiming at the vibration beyond standard limit problems of a missile turbofan engine, one-dimensional finite element beam modeling was built, and the failure was analyzed and simulated in combination with the test data. The results show that the front and back support stiffness of the compressor has a great influence on the second critical speed of the system, which caused by the unsuitable support stiffness within the operation speed, and the overall engine excesses the vibration standard limit. Therefore, it is an effective way to reduce the failure by controlling assembly accuracy of the stiffness.

关 键 词：整机振动 动力学建模 有限元模型 故障分析 临界转速 装配精度 弹用涡扇发动机 

分 类 号：V231.9[航空宇航科学与技术—航空宇航推进理论与工程]