张 帅.基于模型参数辨识的航空发动机风扇叶片裂纹故障诊断[J].航空发动机,2023,49(1):115-121 |
基于模型参数辨识的航空发动机风扇叶片裂纹故障诊断 |
Crack Diagnosis of Aeroengine Fan Blade Based on Model Parameter Identification |
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DOI: |
中文关键词: 叶片裂纹 故障诊断 阻尼 参数辨识 遗传算法 航空发动机 |
英文关键词:blade crack fault diagnosis damping parameter identification genetic algorithm aeroengine |
基金项目:装备预研中航工业联合基金(6141B05110404)资助 |
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中文摘要: |
为了对发动机风扇叶片裂纹故障进行精确诊断,在航空发动机故障模拟试验平台上开展了风扇叶片裂纹故障模拟试
验,对风扇转子叶片进行典型裂纹故障预置,并对风扇转子叶片产生裂纹前后的叶片典型参数进行试验测量。通过风扇转子叶片
阻尼系统及裂纹故障特征理论分析发现,裂纹叶片的模态质量和模态刚度变化会使叶片阻尼比发生明显变化。采用基于遗传算
法的模型参数辨识方法辨识风扇叶片应变响应函数,进而获取风扇叶片阻尼比。结果表明:相同叶片不同次测量试验得到的叶片
阻尼比相差0.02%;不同叶片个体差异导致的阻尼比最大相差2.9%;5#风扇叶片产生裂纹后的阻尼比减小了6.4%。可见,叶片的
阻尼比对其几何特性的变化十分敏感,且通过对风扇叶片阻尼比进行模型参数对应的遗传算法辨识能够实现风扇叶片裂纹故障
诊断。 |
英文摘要: |
In order to accurately diagnose the crack fault of engine fan blade,the fan blade crack fault simulation test was carried out
on the aeroengine fault simulation test platform,the typical crack fault of fan rotor blade was preset,and the typical parameters of the fan
rotor blade before and after the occurrence of crack were measured. Through theoretical analysis of the fan rotor blade damping system and
the crack fault characteristics,it was found that the changes of the modal mass and modal stiffness of the cracked blade would significantly
change the damping ratio of the blade. The model parameter identification method based on genetic algorithm was used to identify the fan
blade strain response function,and then obtain the fan blade damping ratio. The results show that the range of damping ratios of the same
blade from different measurements is 0.02%. The range of damping ratios of different blades is 2.9%. The damping ratio of the No.5 fan
blade after cracks is reduced by 6.4%. It can be seen that the damping ratio of the fan blade is very sensitive to the change of its geometric
characteristics,and the fault diagnosis of the fan blade crack can be realized through the genetic algorithm identification of the model pa?
rameters corresponding to the damping ratio of the fan blade. |
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