可调喷口双模态冲压发动机试验研究

李大鹏; 潘余; 吴继平; 刘卫东; 王振国

可调喷口双模态冲压发动机试验研究

国防科学技术大学航天与材料工程学院, 长沙 410073

基金项目: 国家863高技术计划资助项目

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出版历程
- 收稿日期: 2006-04-05
- 修回日期: 2006-07-14
- 刊出日期: 2007-04-28

Experimental study of a variable-area propelling nozzle dual-mode ramjet

Institute of Aerospace and Material Engineering, National University of Defence Technology, Changsha 410073, China

摘要

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.
- 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
Abstract: 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 supersonic 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.
- aerospace propulsion system /
- variable-area propelling nozzle /
- ignition /
- subsonic combustion /
- supersonic combustion /
- mode transition /
- dual-mode

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参考文献(6)

[1]	Curran E T,Murthy S N B.Scramjet propulsion[M].Progress in Astronautics and Aeronautics,Volume 189,2000.
[2]	FALEMPIN F,SERRE L.The french PROMETHEE program main goals and status in 1999[R].AIAA 99-4814.
[3]	乐嘉陵,胡欲立,刘陵.双模态超燃冲压发动机研究进展[J].流体力学实验与测量,2000,14(1):1-12.LE Jialing,HU Yuli,LIU Ling.Investigation of possibility in developing dual-mode scramjets[J].Measurements in Fluid Mechanics,2000,14(1):1-12.
[4]	范文正,李明.推力矢量喷管现状和发展趋势[J].航空科学与技术,2006,1:21-22.FAN Wenzheng,LI Ming.Status and trends of the thrust-vectoring nozzle[J].Aeronautics Science and Technology,2006(1):21-22.
[5]	丁猛,余勇,梁剑寒,等.碳氢燃料超燃冲压发动机点火技术试验[J].推进技术,2004,25(6):566-569.DING Meng,YU Yong,LIANG Jianhan et al.Experimental investigation of ignition technology in liquid hydrocarbon fueled scramjet combustor[J].Journal of Propulsion Technology,2004,25(6):566-569.
[6]	丁猛.基于凹腔的超声速燃烧火焰稳定技术研究[D].长沙:国防科技大学研究生院,2005.DING Meng.Research on the flame holding technology based on cavity in supersonic combustion[D].Changsha:Doctoral Thesis of Engineering,National University of Defense Technology,2005.