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.