几何可调喉道双模态冲压发动机点火过程试验研究  

Ignition Experimental Study of a Variable Geometrical Throat Dual-mode Ramjet

作　　者：李大鹏[1] 潘余[1] 吴继平[1] 刘卫东[1] 王振国[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,长沙410073

出　　处：《弹箭与制导学报》2006年第4期210-213,217,共5页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：国家863高技术计划资助项目(2003AA723073)

摘　　要：在模拟飞行马赫数Ma=6、高度25km的条件下,文中针对几何可调喉道液体碳氢燃料双模态冲压模型发动机进行了点火过程的直连式试验研究。结果表明:借助几何可调喉道,可以提高模型发动机的点火性能,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驻留,通过几何喉道的调节,模型发动机可以平稳地实现亚燃/超燃间的模态转换过程。采用可变几何喉道结构对于简化几何完全可调双模态冲压发动机的设计、提高现有固定几何双模态冲压发动机的工作范围也具有一定参考价值。Several direct-connect ignition experiments were done for a variable geometrical throat dual-mode ramjet model combustor on the simulated fly condition of Ma= 6 and H=25km. By use of the variable geometrical throat, ignition performance of the dual-mode combustor was improved. Once flame can be hold in the eombustor during subsonic combustion procedure, the supersonic combustion can be achieved 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 enlarged by the variable geometrical throat which simplified a fully variable dual-mode ramjet.

关 键 词：几何可调喉道 点火 亚燃 超燃 模态转换 双模态 

分 类 号：V434.3[航空宇航科学与技术—航空宇航推进理论与工程]