Abstract The tenon-structured disk is a critical component of the rotor system in aeroengines. Under the repeated cyclic loads and inherent material defects, the disk is susceptible to the initiation of fatigue cracks. The impact of disk cracks on the shaft vibration response is subtle and challenging to monitor, however, it can induce periodic vibrations in the blades near the crack location. Therefore, this paper proposes a method for crack identification in rotor disks based on Blade Tip Timing (BTT) technology, which allows for the reflection of rotor disk crack parameters (type, location) through the blade tip vibration parameters, enabling online monitoring and fault diagnosis of rotor disk cracks. To guide the implantation of cracks, this study analyzes the weak points of the disk and conducts a comparative analysis of the effects of cracks of different depths on the blade tip vibration characteristics. Experimental validation confirms the accuracy of the proposed method, providing theoretical support for the onboard online identification of cracks in aeroengine disks.
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