固体火箭冲压发动机补燃室冷态流场实验研究

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。

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

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 5°, the circumferential speed increases, making a better mixing.