Abstract
In order to explore the ablation characteristics of C/SiC ceramic composite nozzles in the working environment of liquid rocket engines, 3D C/SiC composite nozzle was prepared by the precursor impregnation pyrolysis(PIP) process, and the ablation test of the nozzle in various working conditions was carried out. The results show that 3D C/SiC composite nozzle can meet the requirements of anti-ablation performance of the liquid rocket engine under various working conditions. The wire ablation rate of nozzle throat is about 3.92×10-4 mm/s; after the hot test vehicle ablation test, a large amount of white matter SiO2 remains on the inlet cylindrical section, convergent section, throat section and expansion section outer surface of the nozzle, and the ablation pit appears in the throat; the ablation mechanisms of C/SiC composites under liquid rocket engine are mainly mechanical erosion ablation and oxidation ablation.
| Translated title of the contribution | Ablation performance of 3D C/SiC composite nozzles under double-component liquid power environment |
|---|---|
| Original language | Chinese (Traditional) |
| Pages (from-to) | 118-126 |
| Number of pages | 9 |
| Journal | Cailiao Gongcheng/Journal of Materials Engineering |
| Volume | 50 |
| Issue number | 2 |
| DOIs | |
| State | Published - 20 Feb 2022 |