Abstract：Aeroengine compressor blade is a kind of typical thin-wall structure. Laser peening (LP) has been proved
to be an efficient surface treatment to improve the fatigue life of blades by inducing compressive residual stress. Laser
peening on blades at present is usually conducted in a double-side simultaneous scanning method to avoid deflection, which
brings 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 the
change of laser intensity, single-side laser peened thin-wall components can be made to bend toward or away from the laser
beam with single-side. The deflection would recover with the other side laser peened in the same parameters. With proper
laser peening parameters, similar distribution of residual compressive stress to the simultaneous method could be induced
on the components, and the final deflection would be within the scope of the accuracy requirement.
王冬宇，胡永祥，姚振强. 薄壁结构双侧异步激光喷丸强化试验研究*[J]. 航空制造技术, 2017, 60(8): 59-63.
WANG Dongyu, HU Yongxiang, YAO Zhenqiang. Experimental Investigation of Double-Side Laser Peening of Thin-Wall Parts With#br# Alternate Side Laser Scanning. Aeronautical Manufacturing Technology, 2017, 60(8): 59-63.
2017, 
