碳/碳化硅燃气舵的烧蚀及抗热震性

Ablation and thermal shock resistance properties of C/SiC jet vane

利用等离子电弧风洞烧蚀实验装置模拟燃气舵的服役环境,考核了碳/碳化硅(C/SiC)燃气舵的烧蚀性能,探讨了燃气舵的烧蚀机理,采用平面薄板模型对燃气舵的抗热震性能进行了初步分析。结果表明:燃气流的流动方向与燃气舵二者之间的夹角对燃气舵线烧蚀率的影响较大,材料的线烧蚀率从前端沿气流方向(垂直燃气舵)的最大值1.007 mm/s下降至厚度方向(平行于燃气舵)的最小值0.052 mm/s,二者相差近20倍;燃气舵的烧蚀机制主要是粒子侵蚀和机械剥蚀共同作用;同时,材料所受到的热应力是引起材料失效的主要原因。

The ablation properties of C/SiC composites jet vane were evaluated using the plasma wind tunnel ablation equipment. The ablation mechanism of C/SiC composites was explored and the thermal shock-resistance of the jet vane was analyzed by plane flake board model. The results show that the angle between the plasma gas flowing direction and jet vane present great influence on the ablation of C/SiC composites. The linear ablation ratio of the composites decreases from the maximal value of 1.007 mm/s at the front direction of jet vane to the minimal value of 0. 052 mm/s at the brim direction of the component. The difference value between these two ablation ratios is at a factor of about 20. The ablation mechanisms of components are particles erosion and mechanical denudation. Material failure is mainly caused by the thermal stress.