In order to study the distribution law of residual stress on foreign object damage (FOD) position in aero engine blades

the simulated blades were designed according to the characteristics of the aero engine blade leading edge. LS-DYNA software was used to simulate and analyze the impacting process of titanium alloy simulated blade at different angles based on Johnson-Cook constitutive and failure models. The damage morphology and macro size were compared between simulating results and FOD test results to verify the correction of the finite element model. The simulated residual stress distribution at the FOD position corresponding to different incident angles was extracted. The results showed that when the incident angle of steel ball was 0°

the contact force and deformation energy were significantly larger than other incident angles

indicating that the material failure and deformation at the skewed notch caused by a certain incident angle impact were less serious than the semi-circular notch formed by the 0° incident angle impact. There was a significant residual tensile stress area at the FOD notch root near the incident surface. As the incident angle increased

the range of the residual tensile stress area gradually expanded

and the maximum value of the residual tensile stress decreased.