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针对某型涡桨发动机在不分解的前提下对齿轮毂进行故障诊断的要求,设计搭建了整机振动测试系统,利用该测试系统在厂内台架和外场飞机上完成了18台次整机振动测试。特别是专门定制了一台模拟故障的发动机减速器并完成了2台次试验。针对实际故障特点,采用了两种分析信号数据的方法,根据3σ准则确定了监控阀值。根据IIR数字滤波器原理,对实测信号进行了特征频带提取与对比分析,确定了一级齿轮毂内齿端啮合频率(1 736 Hz)、外齿端啮合频率(6 458.5 Hz)为特征频率,研究确定了特征频带监控阀值。并根据Hilbert解调定理对减速器振动信号进行解调,对比分析了调制信号幅值,针对在发动机不同状态下有明显差别的的游星架转频四倍频(71.7 Hz)计算其解调特征监控阀值。
According to the requirement of fault diagnosis of a type of turboprop engine without decomposition under the premise of a certain type of turboprop, a complete machine vibration test system was designed and constructed. With this test system, 18 complete machines were completed on the factory bench and the field aircraft Vibration test. In particular, a specially engineered engine retarder simulated and completed two sub-tests. According to the actual fault characteristics, two methods of analyzing the signal data are adopted, and the monitoring threshold is determined according to the 3σ criterion. According to the principle of IIR digital filter, the characteristic frequency band of the measured signal was extracted and compared, and the internal gear tooth meshing frequency (1 736 Hz) and external tooth tooth meshing frequency (6 458.5 Hz) The research identified the characteristic band monitoring threshold. The vibration signal of the reducer is demodulated according to Hilbert ’s demodulation theorem. The amplitude of the modulation signal is compared and analyzed. The demodulation is calculated for the quadrupole frequency (71.7 Hz) which has obvious difference in different states of the engine. Characteristic monitoring threshold.