涡流阀变推力发动机涡流室涡流结构分析  

Analysis of vortex structure in vortex chamber of variable-thrust motor

作　　者：魏祥庚[1] 李江[1] 陈剑[1] 何国强[1] 

机构地区：[1]西北工业大学燃烧热结构与内流场重点实验室,西安710072

出　　处：《固体火箭技术》2011年第4期443-447,共5页Journal of Solid Rocket Technology

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.

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 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]