Electron Microanalysis of Fracture Surface of Tailing Spout Regulation of Aircraft Engine

The fracture of the tailing spout regulation of aircraft engine was analyzed by scanning electronic microscopy (SEM) and energy dispersive X-ray analyses (EDAX). It was observed that the damage mechanism of fretting fatigue failure was discussed. The damage regulation edge was caused by adhesive wear, and the center part of regulation was damaged by contact fatigue. Fretting fatigue crack initiation tended to occur in fretting scar, especially from grinding pits. There were two factors responsible for specimen damage, one was the plastic deformation of the material layers adjacent to the contact surface caused by normal stress and tangential friction, another was the effect of notch stress concentration caused by surface damage.