固体火箭冲压发动机补燃室冷态流场实验研究  

Experimental study of mixing flow in afterburning chamber of solid rocket ramjet in cold flows

作　　者：胡春波[1] 韩新波[1] 何洪庆[1] 濮思康[1] 杨玉新[1] 

机构地区：[1]西北工业大学航天工程学院,陕西西安710072

出　　处：《推进技术》2004年第2期111-113,117,共4页Journal of Propulsion Technology

基　　金：国家重点实验室基金资助项目(99JS60 3 1ZS6005)。

摘　　要：利用相位多普勒粒子分析仪,在球缺型多级多切轴向喷孔与双侧下颚进气道相配合的实验模型上,测量了固体火箭冲压发动机补燃室内气流掺混流场。通过减小测量壁面厚度解决了曲面上激光聚焦问题。实验结果表明:(1)旋流角度为0°,在进气道一侧下游区域有一较大的回流区,这是由于进气道气流流入补燃室时,其流动方向与补燃室壁面有一夹角,流动方向出现一突扩区域所致。(2)有旋流时,补燃室通过轴线截面上回流区域减小,强度减弱,但沿轴线横截面上,回流强度增强。An model with two submaxillary air inlets and gas nozzles was designed. By Phase Doppler Particles Analyzer, cold flow field in afterburning chamber was measured. The results show that: (1) Without swirl, a big reverse flow region exists downstream on the side of air inlets in section through axis of afterburning chamber, which influences the mixing flow. In the case of 5° swirl, the reverse flow region is smaller and weaker. (2)Without swirl, the circumferential speed is smaller than axial speed, so the mixing effect is not strong. In the case of swirl 5°, the circumferential speed increases, making a better mixing.

关 键 词：固体燃料冲压发动机 加力燃烧室 流动分布 测量 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]