The compressor blade is a vital component of the aero-engine. This is a curved, thin-walled structural component that may undergo deformation after machining. Deformation prediction is essential for studying the deformation caused by residual stresses in compressor blades. This paper investigates the prediction of deformation caused by residual stresses based on the shot peening time sequential (path and sequence) under actual shot peening conditions. The compressor blade as a target for shot peening and measuring residual stresses on its surface and superficial layers. The equivalent residual stresses after shot peening were calculated based on the principle of equal moments. The equivalent residual stresses were loaded onto the blade model based on the shot peening time sequential in the finite element simulation analysis (FEA) to simulate the deformation. The model’s feasibility was confirmed by comparing the simulated deformation with the measured blade deformation. The shot peening time sequential of the blade was then optimized using this model. The prediction of shot peening deformation of compressor blades based on time-sequential loading residual stresses is a crucial reference value for studying residual stress deformation in blade machining. This study can also be applied to other processes besides shot peening.