超燃冲压发动机凹腔内补氧的强化点火试验

推进技术 ›› 2013, Vol. 34 ›› Issue (4): 506-511.

超燃冲压发动机凹腔内补氧的强化点火试验

席文雄,王振国,李庆,刘卫东

国防科学技术大学,高超声速冲压发动机技术重点实验室,湖南长沙 410073;国防科学技术大学,高超声速冲压发动机技术重点实验室,湖南长沙 410073;国防科学技术大学,高超声速冲压发动机技术重点实验室,湖南长沙 410073;国防科学技术大学,高超声速冲压发动机技术重点实验室,湖南长沙 410073

发布日期:2021-08-15
作者简介:席文雄(1984—),男,博士生,研究领域为超燃冲压发动机燃烧过程。E-mail:xwx1984@yahoo.com.cn
基金资助:
国家自然科学基金 (11102230)。

Enhanced Ignition Experiment with Oxygen Addition into Cavity in Scramjet

Science and Technology on Scramjet Laboratory, National University of Defence Technology,Changsha 410073, China;Science and Technology on Scramjet Laboratory, National University of Defence Technology,Changsha 410073, China;Science and Technology on Scramjet Laboratory, National University of Defence Technology,Changsha 410073, China;Science and Technology on Scramjet Laboratory, National University of Defence Technology,Changsha 410073, China

Published:2021-08-15

摘要/Abstract

摘要： 在超燃冲压发动机扩张型燃烧室中,对凹腔内局部补氧的点火强化方法进行了试验研究。采用高速摄影手段研究了不同的补氧方式对凹腔内火焰分布特征和燃烧强度的影响,并针对并联双凹腔燃烧室构型,研究了在单侧凹腔补氧条件下向异侧凹腔的火焰传播过程。试验结果表明,采用凹腔内补氧的方式能调节凹腔内的燃料浓度分布、改善凹腔内的燃烧过程,控制燃烧放热强度；稳态燃烧情况下,观察到凹腔驻留火焰的两种存在特征,分别表现为:由回流区热量反馈机制作用下的凹腔局部驻留火焰和燃烧室全局压力反馈影响下的凹腔剪切层火焰。只有在单侧凹腔燃烧建立了全局压力反馈的条件下才能实现凹腔火焰的异侧传播。 

关键词: 超燃冲压发动机;燃烧室;点火;火焰传播;凹腔;实验研究 

Abstract: Enhanced ignition with oxygen addition into cavity in expanding combustor of scramjet was conducted experimentally. The effects of different methods of oxygen addition on the characteristic of flame distribution and intensity of combustion in cavity were investigated with high speed camera. For combustor with double cavities installed in parallel, the process of flame spread from the side of cavity with oxygen addition to the opposite one was observed. Results confirm that the performance of cold-start in combustor can be improved with oxygen addition which can intensify the combustion within cavity due to modulation of the fuel concentration distribution. Once stable combustion obtained, two types of flame existing in cavity can be distinguished, namely trapped flame within cavity due to local feedback of heat release in recirculation zone and flame surrounding the shear layer because of full feedback of pressure response in the whole combustor. For double-cavity-combustor, the first step of fully pressure established circumstance in single cavity is necessary for flame propagation to the other side. 

Key words: Scramjet;Combustor;Ignition; Flame propagation; Cavity;Experimental research

席文雄,王振国,李庆,刘卫东. 超燃冲压发动机凹腔内补氧的强化点火试验[J]. 推进技术, 2013, 34(4): 506-511.

XI Wen-xiong,WANG Zhen-guo,LI Qing,LIU Wei-dong. Enhanced Ignition Experiment with Oxygen Addition into Cavity in Scramjet[J]. Journal of Propulsion Technology, 2013, 34(4): 506-511.

参考文献

[1] Aggarwal S K.A Review of Spray Ignition Phenomena:Present Status and Future Research[J].Progress in Energy and Combustor Science, 1998,4:565-600.
[2] Situ M, Wang C, Lu H P, et al.Hot Gas Piloted Energy for Supersonic Combustion of Kerosene with Dual-Cavity[R].AIAA 2001-0523.
[3] Kan Kobayashi,Sadatake Tomiokat,Tohru Mitani,et al.Ignition by an H₂/O₂-Microburner in a Supersonic Airflow[R].AIAA 2001-1763.
[4] Kan Kobayashi, Sadatake Tomioka, Tohru Mitani.Supersonic Flow Ignition by Plasma Torch and H₂/O₂Torch[J].Journal of Propulsion and Power,2004,0(2):294-301.
[5] Jian Li, Fuhua Ma, Vigor Yang.Control and Optimization of Ignition Transient in Scramjet Engine Using Air Throttling[R].AIAA 2006-1028.
[6] Zhang M, Hu Z W, Luo K H, et al.LES of Kerosene Spray Combustion with Pilot Flame in a Model Dual Mode Ramjet Chamber[R].AIAA 2009-5385.
[7] 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,2004,5(6):566-569.(DING Meng, YU Yong, LIANG Jian-han,et al.Experimental Investigation of Ignition Technology in Liquid Hydrocarbon Fueled Scramjet Combustor[J].Journal of Propulsion Technology,2004,5(6):566-569.
[8] Lance S J, Campbell D C, Thomas A J.Plasma-Assisted Ignition in Scramjets[J].Journal of Propulsion and Power,2008,4(4):641-654.
[9] 宋文艳,刘伟雄,贺伟,等.超声速燃烧室等离子体点火实验研究[J].实验流体力学,2006,0(4):20-24.
[10] Bernhard H, Michael P, Domenico S.Review of the Potential of Silanes as Rocket/Scramjet Fuels[J].Acta Astronautica,2008,3:379-388.
[11] Morris N A, Morgan F G, Paul A, et al.Silane as an Ignition Aid in Scramjets[R].AIAA 87-1636.
[12] 潘余,刘卫东,梁剑寒,等.模型超燃冲压发动机内着火过程分析[J].力学学报,2009,41(4):455-462.
[13] 席文雄,王振国,刘卫东,等.双模态超燃冲压发动机点火方案对比试验[J].推进技术,2013,34(3):383-389.(XI Wen-xiong,WANG Zhen-guo,LIU Wei-dong,et al.Experimental Comparison on the Scheme of Ignition in Dual-Mode Scramjet[J].Journal of Propulsion Technology,2013,4(3):383-389.)
[14] Shuhei Takahashi, Kazunori Wakai, Sadatake Tomioka.Effects of Combustion on Flowfield in a Model Scramjet Combustor[C].USA:Twenty-Seventh Symposium (International) on Combustion/The Combustion Institute,1998:2143-2150.