双燃烧室固体燃料超声速燃烧研究  

Investigation of Supersonic Combustion of Solid Fuel in Dual Combustor

作　　者：孙海刚[1] 贺永杰[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471000

出　　处：《弹箭与制导学报》2014年第4期125-128,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为了研究亚/超燃空气流量比、空燃比、二次燃气入射角度和等直段长度等因素对燃烧室性能的影响,对固体燃料双燃烧室内流场进行了仿真研究,并开展了固体燃料双燃烧室超声速燃烧原理性验证试验。研究表明,存在最佳的亚/超燃空气流量比,使得燃烧室性能最佳;减小空燃比,尤其是采用二次燃料喷射,增加等直段长度,均可以提高燃烧室的燃烧效率;试验表明,固体燃料在超燃室内能够成功点火,并建立正常的超声速燃烧。In order to analyze the influence of different factors such as sub/supersonic inlet air flow ratio, air-fuel ratio, secondary fuel injection and the straight length on combustion efficiency, a numerical simulation study of supersonic combustion of solid fuel in dual combustor was conducted and then the experiment was carried out. The results show that an optimal flow matching exists in the design of superson- ic inlet and combustor; it can evidently improve combustion efficiency by reducing air-fuel ratio, using of the secondary fuel injection and increasing the straight length, and can improve the combustion efficiency; Solid fuel can be successfully ignited, and the supersonic com- bustion is established in the supersonic combustor.

关 键 词：固体燃料 双燃烧室冲压发动机 超声速燃烧 数值仿真 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]