Abstract: For aero-engines serving in coastal areas, hot-end components such as turbine blades are in a high-temperature, high-pressure, and corrosive operating environment. The surface of turbine components is particularly susceptible to thermal corrosion, which can lead to the deterioration of the mechanical properties of turbine component materials and reduction in structural strength. The distribution law of corrosion pits was analyzed and the finite element model with multiple corrosion pits was established to study the distribution law of stress along with the randomly distributed corrosion pits based on the thermal corrosion morphology diagram of turbine blades in this study. The results indicate that the size and spacing distribution of corrosion pits conform to the lognormal normal distribution law. For multiple corrosion pits under four distribution rules, i.e. regular distribution, irregular size distribution, irregular position distribution, and random distribution, the stress concentration areas appeared in the densely populated areas of corrosion pits, and obvious interference phenomena appeared in the direction perpendicular to the force loading.