<p>Thermal barrier coatings (TBCs) applied to turbine blades in aviation engines and gas turbines often experience erosion damage from small solid particles. This damage is directly linked to the microscale pores randomly distributed within the TBCs, impacting their erosion resistance. The effects of pore-related parameters, such as radius, porosity, and distribution pattern, on the particle impact resistance of Air Plasma-Sprayed Thermal Barrier Coatings (APS-TBCs) using finite element simulations under high-temperature conditions, taking into account the particle initial velocity and incidence angle in this study. The results reveal that changes in pore structure and porosity significantly affect the erosion damage of coatings. In general, the relationship between crack propagation length and particle erosion velocity satisfies an exponential function. In addition, the material loss (Δm) of the coatings exhibits significant fluctuations with the increasing pore radius (0–1 μm), and the optimal pore radius is 0.3 μm for superior erosion resistance; The Δm is achieved around 4% porosity, after which the Δm tends to stabilize with increasing porosity. Additionally, the obtained results show that more pores in the upper layer or near the impact zone lead to more severe erosion, while the erosion quality of the coating increases with the increase of the erosion angle.</p>