摘要
为了研究涡流阀变推力发动机涡流室流动,利用建立的径向压强测试实验装置和三维数值计算模型,进行了涡流室压强分布和涡流结构的研究,获得了涡流室径向压强分布及涡流室旋涡结构。研究结果表明,涡流室内压强分布呈现出中心较小区域变化剧烈,而其余大部分区域变化不明显的现象;流场中心区域存在涡核结构,减小了喷管有效喉部面积,即实现推力调节的有利因素。研究获得计算模型及结论为后续开展涡流阀变推力发动机调节机理分析提供了支撑。
In order to analyze the flow of vortex chamber of variable-thrust motor with the established experiment device and the three-dimensional numerical model,researches on vortex structure and pressure distribution of vortex chamber are carried out.And the results show that the pressure only changes acutely in the middle small region of vortex chamber;the valid throat area of nozzle can be reduced because of the existence of vortex core in middle region of flow field.The numerical model and the conclusion are meaningful for further researches on adjustment mechanism of variable-thrust motor.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2011年第4期443-447,共5页
Journal of Solid Rocket Technology
关键词
固体火箭发动机
变推力发动机
推力调节
涡流阀
涡流结构
solid rocket motor
variable thrust motor
thrust modulation
vortex valve
vortex structure