超声速预混可燃气流的点火与燃烧  

IGNITION AND COMBUSTION OF SUPERSONIC PREMIXED HYDROCARBON FUEL-AIR MIXTURE

作　　者：孙英英[1] 琚诒光[1] 韩肇元[2] 司徒明[3] 

机构地区：[1]清华大学工程力学系,北京100084 [2]中国科技大学力学和机械工程系,安徽合肥230027 [3]航天机电集团公司,31所北京100074

出　　处：《工程热物理学报》2002年第6期776-778,共3页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.19882005);国家"863"航天领域资助项目(No.863-2.99.9

摘　　要：在激波风洞一激波管组合设备上开展了碳氢燃料超声速预混可燃气流的点火与燃烧实验研究。实验结果表明:利用激波对燃料进行预热,并以高温燃气作为引导火焰,可以有效缩短汽油空气超声速可燃混气的点火延迟时间,使之缩短到 0.2 ms以下。利用纹影照片对超声速燃烧流场结构作出了分析;研究了超声速预混可燃气流的温度以及当量比对超声速燃烧流场结构、点火与火焰传播特性的影响。Experimental investigation on ignition and combustion of supersonic premixed hydrocarbon fuel-air mixture has been conducted in the combination facility consisting of a shock tunnel and a shock tube. The experimental results showed that the ignition delay of supersonic premixed gasoline-air mixture could be effectively shortened to less than 0.2 ms through preheating fuel by shock waves and by using hot gas as pilot flame. The structure of supersonic combustion flow field was investigated with the Schlieren pictures. The effects of temperature and equivalence ratio of supersonic premixed combustible flow on the structure of supersonic combustion flow field, ignition and flame propagation were studied.

关 键 词：超声速预混可燃气流 碳氢燃料 点火 超声速燃烧 激波风洞 激光管 

分 类 号：TK16[动力工程及工程热物理—热能工程] V312.1[航空宇航科学与技术—航空宇航推进理论与工程]