航空发动机故障融合诊断研究

结合气路诊断与振动分析方法,建立发动机故障融合诊断模型,探讨气路与振动故障融合诊断方法的可行性。构建故障融合诊断3级体系(故障特征级、故障模式级以及故障决策级融合),实现基于性能参数和振动参数的综合评估方法,获得基于小偏差法的气路故障判据,形成基于动力学分析的振动故障判据,提出故障特征融合的方法,通过算法实现故障融合识别,并在模拟试验器上进行涡轮叶片掉块故障试验验证,获得相应的故障诊断决策。结果表明:设计的发动机故障融合诊断方法合理,算法正确。

Investigation of Aeroengine Fault Fusion Diagnosis

In order to study aeroengine fault diagnosis with information fusion, a health integrated assessment model of aircraft engine based on performance parameters and vibration parameters was established. A three-level system of fault fusion diagnosis was built, including the feature level, mode level and the decision level. A gas path failure criterion based on small deviation method was gained and a vibration failure criterion based on dynamics analysis was formed. A fault fusion diagnosis method was put forward, and a goal of fault fusion recognition through algorithm was achieved. An experiment of turbine blade fracture failure on the rotor experimental device was conducted, and a fault diagnostic decision can be attained. The experiment results indicate that the aeroengine fault fusion diagnosis method is reasonable and the algorithm is correct