Abstract: Experimental investigation on supersonic combustion of kerosene was conducted using fuel-rich hot gas as pilot flame on direct-connect supersonic combustion facility.Based on the measured wall static pressure,experimental data were interpreted using one-dimensional theoretical model combustion efficiency and total pressure recovery coefficient were obtained.The characteristic of static pressure profiles in supersonic combustor was analyzed.The effects of supersonic flow temperature,fuel injection location,and global equivalence ratio on combustor performances were discussed.

Key words: Supersonic combustion ramjet engine;Hydrocarbon fuel combustion;Supersonic combustion;Fuel-rich hot gas;Pilot flame

摘要： 对采用高温富油燃气作引导火焰的煤油超声速燃烧进行了研究。根据试验测得的壁面静压分布 ,采用一维简化模型处理与分析数据 ,得出了不同试验条件下的燃烧效率与总压恢复系数 ;对超声速燃烧室内的静压分布特点作出了分析 ;对超声速燃烧室入口处的气流总温 ,燃料喷射位置 ,以及燃料总体当量比对燃烧室内静压分布、燃烧效率与总压恢复系数的影响进行了讨论。

关键词: 超音速冲压喷气发动机;烃类燃料燃烧;超声速燃烧;高温富油燃气;引导火焰