The dominant factor of C/SiC composites in ablation environment with heat and particle flow

As thermal structure components in scramjet engines, carbon-reinforced silicon carbide (C/SiC) composites are often subject to an ablation coupled with heat and particle flows. This study simulates the working environment of the scramjet engine's thermal structure component by coupling an Al2O3 particle flow with a plasma flow. The ablation behaviour of C/SiC composites in the presence and absence of particle impact have been comprehensively analysed. The results show that the factor dominating the ablation behaviour varies with temperature. At relatively low temperatures, the particles have difficulty breaking down the dense SiO2 layer formed from the oxidation of SiC in the presence of heat flow which is the dominant factor. As the temperature rises, the SiC begins to shift towards active oxidation. A few defects appear in the oxide layer, leading to a significant particle mechanical flaking effect. Particle flow is the dominant factor. However, a higher temperature led to the substantial active oxidation of SiC, and the oxide layer dissipated, exposing more defects. The heat flow causes a strong oxidation reaction, and the scouring effect of the particles is significant as well, both of which play a dominant role in the ablation process.