利用扫描电子显微镜及附带的能谱分析仪对飞机发动机尾喷口调节片断口进行了微观分析研究。结果表明: 调节片边缘的损伤特征以磨损为主,而中部则以接触疲劳为主,疲劳裂纹易在微动区产生。根据上述结果讨论了促使疲劳裂纹萌生的因素,即循环应力和摩擦力引起材料表层塑性变形,以及磨损破坏了材料表面的完整性,造成裂纹尖端应力集中效应。

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.