Abstract: An experimental study was carried out to investigate the supersonic combustion of hydrocarbon fuel(kerosene)in dual combustor at the different air total temperatures of 900 K, 1 340 K and 1 700 K,which were similar to vehicle flight Ma =4,5 and 6.The experiments were set on the ground connected pipe test station of air mass rate 1 2 kg/s.The fuel was injected into subsonic dump combustor.After burned,the fuel riched hot gas flow of Mach number 1 25 was parallel with the main supersonic air flow of Mach number 2 15(or 2 13)in the supersonic combustor.The effects of fuel equivalence ratio on the subsonic and supersonic combustions were investigated for the different total temperatures of air flows.Results show that realization of supersonic combustion of kerosene fuel is possible in dual combutor.

Key words: Supersonic combustion ramjet engine;Supersonic combustion;Subsonic combustion;Cruise missile;Kerosene

摘要： 在空气流量１．２ ｋｇ／ｓ 左右的地面连管试验台上， 进行了模拟飞行Ｍａ＝ ４， ５， ６的三个气流总温状态的碳氢燃料（煤油） 超燃试验。试验用双燃烧室方案， 由突扩型亚燃燃烧室燃烧产生的高温可燃气以马赫数１．２５喷入超燃室， 超燃室空气流马赫数为２．１５ （或２．１３）。不同空气流总温状态下燃料当量比对亚燃燃烧室和超燃燃烧室的试验结果表明， 双燃烧室方案实施煤油的超声速燃烧是可行的。若进一步采取混合增强和合理控制油量分配等措施， 则可提高双燃燃烧室超燃效率。

关键词: 超音速冲压喷气发动机;超音速燃烧;亚音速燃烧;巡航导弹;煤油