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航空发动机压气机叶片是典型薄壁结构,通过激光喷丸强化在叶缘引入残余压应力,是提高其抗异物撞击能力,延长疲劳寿命的有效途径。为解决双侧同步强化方法存在的材料层裂损伤风险的问题,提出薄壁结构双侧异步激光喷丸强化方法。试验研究发现:单侧薄壁激光喷丸试验中,光斑功率密度的改变会使薄壁结构相对于激光入射方向呈现“∧”或“∨”两种扭曲变形趋势;另一面采用同样参数进行激光喷丸后,扭曲变形会恢复;合理采用激光喷丸参数,双侧异步激光喷丸强化与同步强化相似,可以在两侧表面均得到残余压应力场,并且扭曲变形能满足形状精度要求。
Aeroengine compressor blade is a typical thin-walled structure, the introduction of residual compressive stress in the edge of the blade by laser peening is an effective way to improve its anti-foreign impact ability and extend the fatigue life. In order to solve the problem of the damage risk of material splitting existing in the bilateral synchronous strengthening method, a double-sided asynchronous laser shot peening method with thin-walled structure is proposed. The experimental results show that the change of the spot power density in the thin-wall laser shot peening experiment results in the twisting deformation of thin-walled structure relative to the incident direction of laser light, and the other side adopts The same parameters of laser peening, the distortion will be restored; reasonable use of laser peening parameters, the two-phase asynchronous laser peening and synchronous strengthening similar to the surface can be obtained on both sides of the residual compressive stress field, and distortion to meet the shape Accuracy requirements.