轴对称凹腔燃烧室点火影响因素的试验研究  

Experimental Investigation of Effects on Ignition in an Axisymmetric Ramjet Combustor Based on Cavity

作　　者：席文雄[1] 李庆[1] 潘余[1] 谭建国[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》2009年第5期162-165,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：对采用凹腔作为火焰稳定器的亚燃燃烧室进行了点火试验研究。通过考察不同的凹腔结构及其组合方式、煤油喷注方式,分析了凹腔大小、火焰的轴向、周向传播对点火性能的影响。结果表明,点火瞬间的凹腔有效储能大小来源于轴向容积比率;凹腔内的轴向火焰传播是火焰发展的主要机制;在凹腔前方壁面以使喷油能使凹腔内维持合适的燃油浓度分布,是可靠点火的前提。The ignition experiment of an axis-symmetric ramjet eombustor in which cavity was adopted as flameholder was conducted. The size of cavity and mechanism of flame spread were analyzed through ignition investigation on various cavity structures and kerosene injection schemes. The result shows that the instant stored-up energy within the cavity is determined by the volume ratio of axial size. The flame spread in the axial direction is more effective than that in the circumferential direction, which is necessary for establishment of combustion. The proper kerosene distribution in the cavity depends on the kerosene wall-injection scheme before the cavity, which is also a prerequisite for ignition.

关 键 词：凹腔 火焰稳定器 点火 亚燃燃烧室 

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]