RBCC发动机亚燃模态一次火箭引导燃烧的实验

徐朝启; 何国强; 刘佩进; 秦飞; 潘科玮

RBCC发动机亚燃模态一次火箭引导燃烧的实验

西北工业大学燃烧、流动和热结构重点实验室,西安 710072

计量
- 文章访问数: 1857
- HTML浏览量: 91
- PDF量: 1098
- 被引次数: 0
出版历程
- 收稿日期: 2012-04-16
- 刊出日期: 2013-03-28

Experiment of primary rocket-piloting combustion under ramjet-mode condition in RBCC

Science and Technology on Combustion, Internal Flow and Thermo-Structure Laboratory, Northwestern Polytechnical University, Xi'an 710072, China

摘要

摘要: 针对使用液体煤油燃料(JP-10)的火箭基组合动力循环(RBCC)发动机在亚燃模态下使用一次火箭作为引导的燃烧组织开展了实验研究.实验在低来流总温条件下,使用小流量一次火箭羽流作为引导火焰可以实现液体煤油的可靠点火和稳定燃烧,并在扩张燃烧室中实现“热力壅塞”,从而完成RBCC发动机亚燃模态的高效燃烧.在目前发动机燃烧室构型下,通过一系列的发动机壁面压力分布曲线和推力增益的比较,研究了凹腔,支板及壁面喷注位置对发动机性能的影响.实验的结果表明:在一次火箭的下游使用支板喷注器可以使得燃料较容易的分布在主流中,并且在一次火焰羽流的引导下可以实现稳定高效的燃烧.支板喷注器的位置对于发动机的性能有很大的影响,在凹腔前壁面横向喷注燃料,有利于RBCC发动机燃烧性能的提升.为了获得较优的发动机亚燃模态性能,需要进一步对燃料的喷注策略开展优化研究.
- 火箭基组合动力循环(RBCC) /
- 亚燃模态 /
- 引导燃烧 /
- 一次火箭 /
- 发动机性能
Abstract: The experimental studies were performed to investigate primary rocket piloting liquid kerosene (JP-10) combustion in rocket-based combined cycle (RBCC) combustor under typical ramjet-mode condition.Due to the low total temperature of incoming airflow in ramjet mode,the primary rocket with relative low mass flowrate was employed as a piloting flame to achieve reliable ignition and stabilized combustion of liquid kerosene (JP-10) in RBCC combustor.The secondary fuel (JP-10) has been injected into airflow by two strut injectors located behind the primary rocket and an upstream cavity flush-wall injector.The effects of cavity and the location position of strut and wall injection have been investigated..The strut injectors make the fuel easily be distributed into main airflow,and the results indicate that the injected fuel can accomplish steady and efficient combustion due to the interaction with the rocket plume.The comparisons of the pressure distributions in the combustor under different injection conditions show that the strut injection plays an important role in the combustion of wall injection fuel,and additional wall injection associated with cavity would improve the performance of RBCC combustor.Moreover,the wall injection location and the distance between the wall injection and cavity need to be further considered to obtain optimal engine performance.
- rocket-based combined cycle(RBCC) /
- ramjet-mode /
- piloting combustion /
- primary rocket /
- engine performance

HTML

参考文献(15)

[1]	秦飞,吕翔,刘佩进,等.火箭基组合推进研究现状与前景[J].推进技术,2010,31(6):660-665. QIN Fei,LV Xiang,LIU Peijin,et al.Research status and perspective of rocket based combined cycle propulsion system[J].Journal of Propulsion Technology,2010,31(6):660-665.(in Chinese)
[2]	何国强,刘佩进,王国辉,等.支板簇引射发动机:21世纪新型航天动力[J].宇航学报,2000,21(S1):111-115. HE Guoqiang,LIU Peijin, WANG Guohui,et al.Strutjet fngine:a new aerospace power for the 21st century [J].Journal of Astronautics,2000,21(S1):111-115.(in Chinese)
[3]	Kouchi T,Kobayashi K,Kudo K,et al.Performance of a RBCC combustor operating in ramjet mode[R].AIAA-2006-4867,2006.
[4]	Kato T,Kanda T,Kobayashi K,et al.Experimental study of downstream combustion ramjet-mode[R].AIAA-2005-0617,2005.
[5]	Kobayashi K,Tomioka S K,Kato T,et al.Performance of a dual-mode combustor with muti-staged fuel injection[R].AIAA-2004-3482,2004.
[6]	Owens M G,Tehranian S,Segal C,et al.Flameholding configurations for kerosene combustion in a Mach 1.8 airflow[J].Journal of Propulsion and Power,1998,14(4):456-461.
[7]	Kay I W,Peschke W T,Guile R N.Hydrocarbon-fueled scramjet combustor investigation[J].Journal of Propulsion and Power,1992,8(2):507-512.
[8]	LIU Yang,HE Guoqiang,LIU Peijing,et al.Influence of primary rocket mass flow rate on performance of RBCC[R].AIAA-2007-5375,2007.
[9]	潘科玮,何国强,刘佩进,等.RBCC混合燃烧模态一次火箭对燃烧稳定的影响[J].推进技术,2010,31(5):544-548. PAN Kewei,HE Guoqiang,LIU Peijin,et al.Influence of combustion stabilization by primary rocket under commix-combustion mode in RBCC[J].Journal of Propulsion Technology,2010,31(5):544-548.(in Chinese)
[10]	潘科玮,何国强,刘佩进,等.发动机燃料喷注位置变化对混合燃烧模式燃烧的影响[J].航空动力学报,2011,26(8):1900-1906. PAN Kewei,HE Guoqiang,LIU Peijin,et al.Numerical investigation of combustion about injection positions in rocket induced secondary combustion of RBCC engine[J].Journal of Aerospace Power,2011,26(8):1900-1906.(in Chinese)
[11]	Sunami T,Magre T,Bresson A,et al.Experimental study of strut injectors in a supersonic combustor using OH-PLIF[R].AIAA-2005-3304,2005.
[12]	Hsu K,Carter C D,Gruber M R,et al.Mixing study of strut injectors in supersonic flows[R].AIAA-2009-5226,2009.
[13]	Doster J C,King P I,Gruber M R,et al.In-stream hypermixer fueling pylons in supersonic flow[J].Journal of Propulsion and Power,2009,25(4):885-901.
[14]	Hsu K Y,Carter C D,Gruber M R,et al.Experimental study of cavity-strut combustion in supersonic flow[J].Journal of Propulsion and Power,2010,26(6):1237-1246.
[15]	Bonnie J M,Gordonk S.Computer program for calculation of complex chemical equilibrium compositions and applications:Ⅱ users manual and program description[R].NASA RP-1311,1996.