摘要
为了研究高静温预混超声速气流中爆轰的机理问题,利用自主设计的连续式加热器来产生马赫数为2.6,静温大于700 K的氢/空气预混超声速气流,并采用高速纹影技术来观测斜激波诱导脱体爆轰的直接起爆和发展的动态过程.研究表明,实验得到的起爆前斜激波和起爆后脱体爆轰波的角度与理论分析结果非常一致.并发现由激波诱导爆燃向激波诱导脱体爆轰的转变过程非常快;而且对于当前初温较高当量比较低的混合物,会出现爆轰波突然熄灭与重新起爆的现象.当前研究为爆轰燃烧在高超声速推进中的应用提供了重要参考.
In order to study the detonation mechanism problems in the elevated initial temperature supersonic flow, a continuous heater was designed and employed to produce supersonic premixed hydrogen/air mixture flow, with Mach number of 2.6 and static temperature above 700K; and the high speed schlieren was used to observe and analyze the direct initiation and development process of the detonation. The result shows that the oblique shock angle before the detonation initiation and the detached detonation angle are consistent with theoretical analysis. It is also found that the transition from the deflagration to detonation in duced by oblique shock is rapid, and the phenomenon of detonation failure and re-initiation will exit under the circumstances of high initial temperature and low stoichiometric ratio of combustible mixture. The results obtained here provide a reference for the application of detonation in the hypersonic propulsion.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第1期50-54,共5页
Journal of Aerospace Power
基金
全国博士学位论文作者专项资金(FANEDD200454)
关键词
脱体爆轰波
激波诱导燃烧
预混超声速加热器
高初始静温
detached detonation
shock induced combustion
premixed supersonic heater
elevated initial static temperature
