摘要
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 kind of typical thin-wall structure.Laser peening(LP)has been provedto be an efficient surface treatment to improve the fatigue life of blades by inducing compressive residual stress.Laserpeening on blades at present is usually conducted in a double-side simultaneous scanning method to avoid deflection,whichbrings the problem that shock waves from dual side meet at the center,resulting in spallation being at high risk to happen.In this paper,a double-side alternate laser peening method is proposed.The results of the experiments show that with thechange of laser intensity,single-side laser peened thin-wall components can be made to bend toward or away from the laserbeam with single-side.The deflection would recover with the other side laser peened in the same parameters.With properlaser peening parameters,similar distribution of residual compressive stress to the simultaneous method could be inducedon the components,and the final deflection would be within the scope of the accuracy requirement.
作者
王冬宇
胡永祥
姚振强
WANG Dongyu;HU Yongxiang;YAO Zhenqiang(State Key Laboratory of Mechanical System and Vibration, School of Mechanical Engineering,Shanghai Jiao Tong University, Shanghai 200240, China)
出处
《航空制造技术》
2017年第8期59-63,共5页
Aeronautical Manufacturing Technology
基金
航空科学基金项目(20145457008)
上海市青年科技启明星计划(16QA1402000)
国家重点研发计划(2016YFB1102705)
关键词
激光喷丸强化
薄壁
变形
残余应力
Laser peening
Thin wall
Deflection
Residual stress
