Abstract: In order to accurately monitor the traveling wave resonance characteristics of the central bevel gear of aero-engine in the complex working environment， and satisfy the technical requirements of small modification of the tester and easy installation of the test device， the derived noise measurement method based on rigid wall acoustic waveguide technology and the dynamic characteristic calibration method based on the principle of substitution method are established. The derived noise measurement system and the dynamic calibration system of digital closed-loop control loudspeaker traveling-wave tube （TWT） device are developed. The problem of noise signal measurement of gear traveling wave resonance and data correction in complex environment are solved. The traveling wave resonance test of the central drive bevel gear in aero-engine based on noise and stress synchronization testing was completed. The traveling wave resonance frequency and the resonance speed as well as the magnitude of acoustic radiation of node-diameter vibration of driven bevel gear are analyzed. The tests results show that the derived noise measurement method and system as well as the dynamic calibration method and system effectively improve the measurement accuracy of traveling wave resonance characteristics of gear. They can realize accurate identification and effective monitoring of traveling wave resonance frequency and resonance speed of gear under high temperature and high oil mist environment. The error of traveling wave resonance frequency is less than 0.04%， and resonance speed is less than 0.005%. The sound pressure energy of the vibration radiation of the gear spoke plate in the case of the backward traveling wave （BTW） of the 4th node-diameter （ND） is 3.5 times greater than that of the forward traveling wave （FTW） of the 3rd ND， which indicates that traveling wave resonance of gear at high speed is more dangerous.

Key words: Aero-engine;Central drive bevel gears;Traveling wave resonance;Accurate identification;Acoustic measurement method

摘要： 为了精准监测复杂工作环境下航空发动机中央传动锥齿轮行波共振特征，并满足对试验器改装小和测试装置易安装的技术要求，建立了基于刚性壁声波导管技术的导出式噪声测量方法和基于替代法原理的动态特性标定方法，研制了导出式噪声测量系统和数字式闭环控制声喇叭行波管装置动态标定系统，解决了复杂环境下的齿轮行波共振声信号测量与数据修正的问题。完成了基于噪声和应力同步测试的航空发动机中央传动锥齿轮行波共振特性试验，对从动锥齿轮的行波共振频率、共振转速及节径振动声辐射量级进行了分析。研究结果表明：导出式噪声测量方法及系统和动态标定方法及系统有效提高了齿轮行波共振特性的测量精度，可实现高温高油雾环境下齿轮行波共振频率和共振转速的精准识别和有效监测，行波共振频率误差<0.04%，共振转速误差<0.005%。四节径后行波共振时的齿轮辐板振动辐射的声压能量是三节径前行波共振时的4.5倍，说明齿轮在高转速发生行波共振会更危险。

关键词: 航空发动机;中央传动锥齿轮;行波共振;精准识别;声测法