M6双模态冲压模型发动机氢燃料的燃烧试验研究

在一个有突扩台阶的氢燃料高超声速冲压发动机模型内研究了氢燃料喷注方式对点火与燃烧效果的影响。氢气从均匀分布于支板上的小孔喷注 ,支板位于燃烧室突扩台阶后 ,燃料的喷注方向可调。本文研究了逆来流喷射、逆流与来流夹 4 5°角喷射 ,同时从支板前端面逆喷和从支板后端面顺喷、从壁面垂直于气流喷注燃料时 ,燃烧室内燃烧效果的差异。实验在中国空气动力研究与发展中心的脉冲燃烧风洞上进行 ,实验马赫数为 6 ,总温1 85 0 K,总压 5 .5 MPa。实验结果表明 ,从支板前端面逆喷氢气时 ,点火与燃烧的效果最好。逆喷方式下 ,当氢气的当量油气比为 0 .8时 ,在本模型流道构型条件下 ,获得的推力收益超过 5 0 0 N。

Experimental Investigation on Combustion in a Hydrogen-Fueled Dual-Mode Scramjet Model at M6

A dual-mode scramjet model engine with a rear-faced step is experimentally investigated with different hydrogen fuel injection manners. The fuel is injected into a combustor from the holes in pylons, which is settled downstream from the rear-face step, with different angles against, parallel or perpendicular to the airflow. The wall pressure and the drag-thrust are measured to investigate the fuel self-ignition and its combustion. The measured data indicate that when hydrogen fuel is injected against the air-flow in the combustor it realizes the strongest self-ignition and combustion. When the equivalent fuel-air ratio achieves to 0 8, thrust of more than 500 N is obtained. Experiment is conducted in Pulse-type Combustion Heated Wind Tunnel in China Aerodynamics Research and Development Center. The free flow parameters are as follows: M number is 6, total temperature 1 850 K,and the total pressure 5 5 MPa.