氢氧火炬式电点火器燃烧流动分析  

Combustion Flow Analysis of the Hydrogen-oxygen Torch Igniter

作　　者：杨进慧 王朝晖[1] 左安军 丁兆波[1] 孙纪国 Yang Jin-hui;Wang Zhao-hui;Zuo An-jun;Ding Zhao-bo;Sun Ji-guo(Beijing Aerospace Propulsion Institute, Beijing, 100076)

机构地区：[1]北京航天动力研究所

出　　处：《导弹与航天运载技术》2019年第3期45-48,共4页Missiles and Space Vehicles

摘　　要：为研究氢氧火炬式电点火器工况范围广、燃烧流场复杂的特性,采用 CFD 数值仿真方法,对不同氢氧喷注距离、混合比以及背压对点火器内燃烧流动及热防护的影响进行了研究。结果表明:氢氧喷注距离的缩短有利于点火器头部及火花塞热防护,但会造成点火器身部内壁温度升高;混合比过高将直接导致火花塞及氧喷嘴烧蚀,需结合点火能量优化设计;流量不变,点火器背压升高对燃烧及热防护影响不大。The hydrogen-oxygen torch igniter operates in wide conditions of pressure and mixture ratio, which results in complicated combustion phenomenon. The influence of hydrogen-oxygen injection distance, mixture ratio and back pressure on igniter combustion and thermal protection are studied by CFD numerical simulation methods. Results reveal that shorter hydrogen-oxygen injection distance is helpful to protect the igniter head and spark plug, while the temperature of igniter chamber wall rises. High mixture ratio results in spark plug and oxygen injector erosion, which should be selected combining with the ignition energy. The back pressure has negligible effects on the igniter combustion and thermal protection with the same mass flow.

关 键 词：点火器 氢氧喷注距离 混合比 背压 热防护 

分 类 号：V434.1[航空宇航科学与技术—航空宇航推进理论与工程]