气氧甲烷火炬式点火器稳态仿真分析  

Steady-state Simulation of GOX/Methane Spark Torch Igniter

作　　者：王铁岩[1] 郑孟伟[1] 蔡振宇[1] 

机构地区：[1]北京航天动力研究所,北京100076

出　　处：《导弹与航天运载技术》2016年第4期63-66,95,共5页Missiles and Space Vehicles

摘　　要：为了对一种气氧甲烷点火器内部燃烧情况进行评估,针对该点火器的燃烧反应、流动及工作特点,应用CFD计算方法进行了稳态仿真分析。该点火器为保证其重复使用可靠性,采用电火花起火点燃高混合比燃气后补燃的设计,此种设计点火器内燃烧环境特殊,流场较为复杂,中国缺乏相应的设计经验。通过数值仿真很好地预测出了点火器的出口温度及烧蚀位置,并为该点火器的改进提供了参考。Aiming at combustion reaction, flow field and work characteristics of the GOX/Methane spark torch igniter, steady-state simulation is conducted in CFD software to evaluate the internal combustion of the igniter. To ensure the reliability of the igniter, secondary combustion is used after firing the high mixing ratio gas by spark ignition. This design is lack of experience in China, the igniter combustion environment is special and flow field is complex. The numerical simulation results can predict the outlet temperature and the ablation location of the igniter, which provides reference for the improvement of the igniter.

关 键 词：液体推进剂火箭发动机 气氧甲烷 点火器 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]