论文部分内容阅读
本实验研究中使用了小型固体推进剂火箭发动机及不同结构参数的喉部组件。用于研究喷管结构因素对喷管喉部沉积的影响.在实验中成功地观察到了喷管喉部沉积的现象.并且获得了结构因素(包括喷管喉衬的厚度、喉部表面的粗糙度,收敛角及喉部过渡圆弧半径)对喷管喉部沉积影响的初步规律.其中.喉衬厚度的影响是最显著的.实验结果为喷管喉部沉积机理的研究提供了依据,并且提出了可用于消除喷管喉部沉积现象的措施.
The experimental study used a small solid propellant rocket engine and throat components with different structural parameters. Which is used to study the influence of nozzle structure on laryngeal deposition of lance.We successfully observed the laryngeal lap deposition in the experiment and obtained the structural factors including the thickness of laryngeal liner, Degree of convergence angle and the transition radius of laryngeal arc) on the laryngeal deposition of the ladle.Among them, the influence of the thickness of the laryngeal line is the most significant.The experimental results provide the basis for the research on laryngeal deposition mechanism of the lance, And put forward the measures that can be used to eliminate the throat deposition phenomenon of the nozzle.