Ablation behavior of a three-dimensional carbon/silicon carbide composite nozzle in an ethanol/oxygen combustion gas generator

The ablation properties of a three-dimensional carbon/silicon carbide composite nozzle were investigated via hot-fire testing by an ethanol/ oxygen combustion gas generator simulating combustion environments of the liquid rocket engine. The linear ablation rate at the nozzle throat was 0.250±0.023mm/s, and the overall mass ablation rate was 0.246kg/(m 2 s). The ablation in the divergent section, convergent section, and in the regions near the throat grew severe by degree. Ablation mechanisms of the composite nozzle were predominated by the oxidation of the composite, and volatilization of the silica scale derived from oxidation of silicon carbide resulted in further ablation of the nozzle.