航空锥齿轮阻尼环减振作用分析与试验验证  

Numerical analysis and experimental verification of damping effect of aeronautical bevel gear with damping ring

作　　者：邱之睿 欧代松 李贵林 QIU Zhirui;OU Daisong;LI Guilin(AECC Sichuan Gas Turbine Establishment,Chengdu 610500)

机构地区：[1]中国航发四川燃气涡轮研究院,成都610500

出　　处：《燃气涡轮试验与研究》2023年第4期36-43,共8页Gas Turbine Experiment and Research

摘　　要：针对航空锥齿轮出现的节径型行波共振问题,通过加装阻尼环对其进行减振,并对减振效果进行仿真分析和试验验证。通过对锥齿轮进行模态分析和振动应力计算,分析附加阻尼环对齿轮行波共振的影响;试验中在齿轮上粘贴应变片,获取齿轮的振动应变。计算与试验结果对比表明,锥齿轮在转速范围内主要存在前4节径行波共振模态,共振转速计算值与试验值误差较小,在共振转速下计算的阻尼减振效果与试验数据接近,满足一定的工程预测要求,验证了该计算方法的有效性,表明附加阻尼环对于行波共振具有良好的抑制作用。To solve the problem of traveling wave resonance in aeronautical bevel gears,a ring damper was installed to reduce the vibration of the gear,and the damping effect was calculated by simulation and verified by experiment.Through modal analysis and calculation of vibration stress,the influence on the traveling wave resonance by adding a ring damper was analyzed.In the test,strain gauges were attached to the gear,and vibration strain was obtained through a system of telemetry.Comparing the calculated and test results,it is found that the bevel gear mainly contains first four pitch radial traveling wave resonant modes within the speed range.The error of resonance speed between calculation and test results is fairly small,and the calculated vibration dissipation under resonance speed is closed to the data of test,which meets certain requirements of engineering prediction and verifies the validation of simulation,indicating that the additional damping ring has a good restraining effect on traveling wave resonance.

关 键 词：航空发动机 齿轮 摩擦减振 行波共振 振动应力 数值仿真 

分 类 号：V263.3[航空宇航科学与技术—航空宇航制造工程]