摘要
在模拟飞行马赫数Ma=6,高度25km的条件下,针对可调喷口液体碳氢燃料双模态冲压模型发动机进行了直连式试验研究.结果表明借助喷口可调机构,可以提高模型发动机的点火性能和推力性能,并且可以在低当量比下实现亚燃模态,而一旦亚燃阶段实现火焰维持,通过喷口截面的调节,模型发动机可以平稳地实现亚燃/超燃间的模态转换过程.采用可调喷口结构对于简化几何完全可调双模态冲压发动机的设计、拓宽现有固定几何双模态冲压发动机的工作范围都具有一定参考价值.
Several direct-connect hot tests were done for a variable-area propelling nozzle dual-mode ramjet model combustor on the simulated fly condition of Ma=6 and H=25 km. By use of the variable-area propelling nozzle, ignition performance and thrust of the dual- mode combustor were improved. Once flame can be hold in the combustor during subsonic combustion procedure, the supers6nic combustion can be achieved by adjusting nozzle area thus a mode transition can be realized also. Finally, It is promising that the operating region of a fixed-geometry dual-mode ramjet can be extended by the variable-area propelling nozzle which simplified a fully variable dual-mode ramjet.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第4期625-631,共7页
Journal of Aerospace Power
基金
国家863高技术计划资助项目
关键词
航空
航天推进系统
可调喷口
点火
亚燃
超燃
模态转换
双模态
aerospace propulsion system
variable-area propelling nozzle
ignition
subsonic combustion
supersonic combustion
mode transition
dual-mode
