ZHANG Shuai.Crack Diagnosis of Aeroengine Fan Blade Based on Model Parameter Identification[J].航空发动机,2023,49(1):115-121 |
Crack Diagnosis of Aeroengine Fan Blade Based on Model Parameter Identification |
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Key Words:blade crack fault diagnosis damping parameter identification genetic algorithm aeroengine |
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Abstract: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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