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
DOI:
Key Words:blade crack  fault diagnosis  damping  parameter identification  genetic algorithm  aeroengine
Author NameAffiliationE-mail
ZHANG Shuai Chinese Flight Test EstablishmentXi’an 710089China 18792788842@163.com 
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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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