| Citation: | YANG Mujin, LU Songbing, YANG Dabing, et al. Fracture analysis of turbine rotor blades in an aircraft engine[J]. Journal of Aerospace Power, 2025, 40（12）：20240062 doi: 10.13224/j.cnki.jasp.20240062
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In response to the occurrence of turbine rotor blade fracture failures during the testing process of an aeroengine, research on the failed turbine rotor was conducted through visual inspection, fluorescence detection, energy spectrum analysis, strength analysis, and blade vibration analysis. It was found that after eliminating factors such as foreign object damage, material defects, and casting process defects, the fracture failure mode of the blade was confirmed as fatigue failure through blade fracture inspection. Through simulation analysis, it was ultimately determined that the cause of blade fatigue failure was the combined effects of static stress generated by centrifugal load and thermal load, and vibration stress caused by high-frequency airflow excitation through the combustion chamber evaporation tube. A scheme was proposed to reduce the number of combustion chamber evaporation tubes and thicken the trailing edge of the turbine rotor blades, reducing the flow excitation frequency so that there was no intersection between the natural frequency of the blades and the excitation frequency within the full speed range, thus avoiding fatigue failure of the turbine rotor blades due to resonance.
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