超音速燃烧室煤油强迫点火试验研究  

Experimental Investigation of Kerosene Ignition and Combustion in Supersonic Combustor

作　　者：宋文艳[1] 曹玉吉[1] 刘伟雄[2] 贺伟[2] 白菡尘[2] 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]中国空气动力研究与发展中心,四川绵阳622663

出　　处：《弹箭与制导学报》2006年第S6期426-428,454,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：利用氢氧燃烧加热脉冲风洞,探索了在超音速燃烧室进口Ma=2、总温T0=960～1 420K条件下.使煤油实现点火和稳定燃烧的方法。分别使用火花塞+先锋氢火焰、火花塞+先锋乙稀火焰,完成了壁面喷射方式的超燃燃烧室煤油点火与稳定燃烧直连式实验,实现了煤油的强迫点火和稳定燃烧。研究表明,在燃烧室进口Ma=2、总温T0=960K时,采用火花塞辅助氢气点火可实现煤油的点火和燃烧。The method for kerosene Ignition and flame stabilization in supersonic combustor was explored in impulse hydrogen/oxygen combustion wind tunnel. The entrance condition of supersonic combustor is Mach number 2. total temperature between 960-1420K. The spark plug with pilot-hydrogen, spark plug with pilot-ethylene were adopted in the direct-connect experiment of supersonic combustor. The kerosene Ignition and flame stabilization was obtained by using wall injection fuel. The experimental results indicate that kerosene can be ignited with spark plug with pilot-hydrogen at entrance stagnation temperature of 960K.

关 键 词：超音速燃烧冲压发动机 点火 超音速燃烧 煤油 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]