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采用激光斜入方法对航空发动机扇轴转接圆角部位进行激光冲击强化试验。分析了斜冲击机理及方法,计算优化斜激光冲击强化试验参数,对冲击前后试件的显微硬度、残余应力进行对比分析,并进行旋转了弯曲疲劳对比验证试验。其结果表明,风扇轴经过激光斜冲击强化后,表面显微硬度提高了11%,残余应力不均匀性得到改善,旋转弯曲疲劳寿命提高了160%;断口观察分析可知,激光冲击强化可以使疲劳源位置内移,降低裂纹扩展速率,从而提高试件的疲劳性能。
The laser oblique penetration method is used to test the laser shock on the fillet part of the aero-engine fan shaft. The oblique impact mechanism and method were analyzed. The parameters of oblique laser shock enhancement were calculated, and the microhardness and residual stress of the specimens before and after impact were analyzed. The bending fatigue comparative test was carried out. The results show that after laser oblique impact strengthening, the microhardness of the surface of the fan shaft increases by 11%, the residual stress nonuniformity improves, and the rotating bending fatigue life increases by 160%. Fracture observation shows that laser shock can enhance the fatigue The source position is shifted inward to reduce the crack growth rate, so as to improve the fatigue property of the specimen.