凹腔火焰稳定器布置方式对超声速燃烧点火的影响  

Effect of Layout of Reentrant Flame Holder on Scramjet Ignition

作　　者：潘余[1] 刘卫东[1] 王振国[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,长沙410073

出　　处：《弹箭与制导学报》2008年第5期135-138,共4页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：863项目资助

摘　　要：在来流马赫数2.64、总温1300K、静压83.3kPa的条件下,通过在燃烧室内安装不同数目的凹腔火焰稳定器来改变燃烧室构型,研究了火花塞点燃氢气、氢气引导火焰点燃煤油、煤油和氢气燃烧火焰点燃更多煤油和煤油稳定燃烧过程。结果表明,小扩张角段更易实现点火;异侧布置的两个凹腔,即使一侧凹腔上未喷射燃料,也具有增强点火和火焰稳定作用;同侧布置两凹腔距离过近不利于点火;燃料着火能力随凹腔数目的增多而增强。The hydrogen ignited by spark plug, kerosene ignited by flame with hydrogen, more kerosene ignited by steady combustion flame and kerosene combustion were investigated by installing different number of cavities at different position of the combustor with the inflow Ma=2.64, total pressure Pt= 1300K and static pressure P= 83.3kPa. Resuhs show it is easier to get successful ignition at the small divergent section; The opposite cavity without fuel injection also enhance the ignition ability. Too close two cavities in tandem is bad for ignition. More cavities lead to better ignition ability.

关 键 词：超声速燃烧冲压发动机 点火 燃烧室构型 凹腔火焰稳定器 

分 类 号：V235.213[航空宇航科学与技术—航空宇航推进理论与工程]