Abstract: Aiming at the driven bevel gear fracture failure of a certain type of aero-engine central drive bevel gear due to traveling wave resonance in actual processes, combination of simulation analysis and test verification was used to study the traveling wave resonance characteristics and influence laws of spiral bevel gears under parameter adjustment. The modal analysis of the driven gears was carried out based on finite element method, and the relationship between the thickness of the spoke plate and the working temperature with the gear traveling wave resonance characteristics was discussed. Transient dynamic analysis of meshing gears was carried out based on Hertz contact theory, and the influences of load power, operating temperature and damping factor on the stress distribution of driven bevel gears under traveling wave resonance were discussed. The comparison of simulation and test results shows that the errors of simulation results of modal calculation and dynamic analysis are within a reasonable range. Under the premise of meeting the relevant requirements of gear design, the resonance speed or resonance frequency may be avoided by adjusting the thickness of the spoke plate. In terms of the sensitivity of the resonance parameters of the vibration stress distribution, the analysis shows that when the gear is working in the third or fourth nodal diameter traveling wave resonance states, the stress values at the tooth roots are the largest, and the stress values on the front surfaces of the spoke plate are the smallest; when the temperature and damping factor changing, the change of stress values at front of the driven bevel gear spoke plate is small, and the change of stress values at the back of the spoke plate and tooth root is big. Therefore, in improvement and optimization designs of the gears, it is necessary to deal with the third or fourth nodal diameter traveling wave resonance.

Key words: aero-engine, spiral bevel gear, traveling wave resonance, resonance frequency, vibration stress

摘要： 针对某型航空发动机中央传动锥齿轮在实际使用中因行波共振造成的从动轮断裂失效问题，采用仿真分析与试验验证相结合的方法，研究弧齿锥齿轮参数调节状态下的行波共振特性及其影响规律。基于有限元方法对齿轮进行模态分析，讨论辐板厚度和工作温度对齿轮行波共振特性的影响；基于Hertz接触理论对啮合齿轮进行瞬态动力学分析，重点讨论行波共振状态下负载功率、工作温度及阻尼系数对齿轮应力分布的影响。仿真与试验对比结果表明：模态计算和动力学分析的仿真结果误差均在合理范围内。在满足齿轮设计有关要求前提下，调整辐板厚度可避开共振转速或共振频率。在振动应力分布的共振参数敏感性方面：当齿轮在三四节径行波共振状态下工作时，齿根处应力值最大，辐板正面应力值最小；随着齿轮负载功率、工作温度和阻尼系数变化，从动轮辐板正面应力变化较小，辐板背面和齿根处变化较大。在该齿轮改进和优化设计中，需重点针对三四节径行波共振进行处理。

关键词: 航空发动机, 弧齿锥齿轮, 行波共振, 共振频率, 振动应力