Fracture Fault Analysis and Test Verification of Engine Compressor Blades

The abnormal phenomenon of higher gas temperature occurred during the process of engine operation, and the compressor rotor blades of stage II and III fractured during later testing. Through decomposition inspection and physical and chemical analysis, the fracture mode and the first failure one of the fractured blades were determined. The fracture cause of the first failure part was analyzed from the aspects of design, manufacturing, assembly and use. And then the fracture cause was verified by the simulation test of higher gas temperature of the whole machine and the measurement test of compressor blade tip amplitude. The results show that high-cycle fatigue fracture occurred to some rotor blades of stage II compressor, which are the first failure parts. There were higher gas temperature and greater first-order bending vibration stress on stage II compressor blades under severe intake distortion condition. Inaccurate angle of adjustable blades and abnormal excitation frequency are the fracture cause of compressor blades.