The work aims to reduce the processing errors of the integral blade disk of the aerospace engine and achieve high precision of the product. A finite element model for the global distribution of processing deformation of the integral disk and blade was established. Considering the coupling effect of tool correction and deformation error during compensation processing, the blade deformation compensation was calculated by a multiple iteration method. A reverse reconstruction geometric model compensation strategy was proposed, which used the compensation amount to reconstruct the blade geometric contour and regenerate the tool path program containing blade deformation error information. The deformation distribution prediction model and the proposed reverse reconstruction model compensation strategy were validated through milling experiments and surface accuracy measurement experiments on the integral blade of a certain aerospace engine. The results showed a good agreement between the predicted results and the experimental results, with an average error of 7.96%. The new compensation strategy data embedding method was efficient and could significantly reduce deformation errors generated during the processing, controlling the precision of the finished product within the allowable tolerance range of the design. The method proposed can significantly improve the milling quality of integral disk and blade, providing higher surface accuracy for subsequent grinding of blade parts.