某航空发动机扭振减振器失效机理分析

Failure Mechanism Analysis of Torsional Vibration Damper in an Aircraft Engine

为了探究某航空发动机曲轴扭振减振器的失效机理,采用有限元法对该发动机轴系进行了模态分析,并进行了试验验证;基于轴系扭纵耦合振动理论和谐响应分析计算了该轴系的轴向振动位移幅值;在此基础上对扭振减振器进行了失效分析。研究结果表明,因该航空发动机经常工作在过渡工况,引起轴系扭转共振和扭纵耦合振动,使得轴系轴向位移较大,轴系产生的轴向力是造成该扭振减振器失效的最主要原因。

In order to explore the failure mechanism of an aircraft engine＇s crankshaft torsional vibration damper, the finite element modal analysis and experimental verification of the engine shafting are carried out. Then, axial vibration displacement amplitude of the shaft is calculated based on coupled torsional-axial vibration theory and harmonic response analysis. On the basis of calculation results is completed. The research results show that the aircraft engine torsional resonance and coupled torsional-axial vibration. The the failure analysis of the torsional vibration damper often works in the transition condition, which causes axial vibration makes the shafting axial displacement larger. The coupled axial force is the main cause of torsional vibration damper failure.