超声速燃烧室乙烯/空气等离子体射流点火试验研究

推进技术 ›› 2017, Vol. 38 ›› Issue (7): 1532-1538.

超声速燃烧室乙烯/空气等离子体射流点火试验研究

刘毅¹,窦志国¹,杨波²,张鹏¹

装备学院激光推进及其应用国家重点实验室，北京 101416,装备学院激光推进及其应用国家重点实验室，北京 101416,中国人民解放军63819部队，四川宜宾 644000,装备学院激光推进及其应用国家重点实验室，北京 101416

发布日期:2021-08-15
作者简介:刘毅，男，硕士生，研究领域为超声速燃烧室等离子体点火助燃技术。

Experimental Investigation on Ignition of Ethylene/Air by Plasma Jet in Supersonic Combustor

State Key Laboratory of Laser Propulsion & Application，Equipment Academy，Beijing 101416，China,State Key Laboratory of Laser Propulsion & Application，Equipment Academy，Beijing 101416，China,The Liberation Army of 63819 Forces，Yibin 644000，China and State Key Laboratory of Laser Propulsion & Application，Equipment Academy，Beijing 101416，China

Published:2021-08-15

摘要/Abstract

摘要： 在来流马赫数1.8，总温800K的超声速燃烧直连式试验台开展了乙烯/空气等离子射流点火的试验研究。采用高速摄影仪拍摄了等离子体射流流场结构、自发光火焰图像和火焰纹影图，对比分析了燃料喷注压力、混合燃料、等离子体射流介质对点火特性的影响。试验结果表明，等离子体射流与主流之间的剪切作用形成了大尺度的涡结构，射流尾流工质主要存在于凹腔剪切层附近，射流与主流干扰的全局特征主要表现在射流诱导的弓形激波上，射流动量的增加，激波强度增强。燃料喷注压力升高，点火后燃烧室稳态压力升高，同时压力响应曲线提前；乙烯喷注压力低于0.33MPa时，压力曲线出现一定震荡，燃烧室无法建立稳定火焰，在0.33～0.624MPa时燃烧过程存在超燃向亚燃燃烧模态转换，高于0.624MPa时点火过程趋于平稳。乙烯和甲烷混合燃料的点火贫油极限出现在喷注压力0.394MPa附近。等离子体射流虽能提供高温工质，但是其射流尾流中经冷空气掺混的部分气体分子将对燃料浓度起到稀释作用，进而影响点火性能。

关键词: 超声速燃烧室；等离子体射流点火；燃料喷注压力；射流介质；点火特性

Abstract: Ignition of ethylene/air by plasma jet was experimentally investigated on directly connected supersonic combustion facility with air total temperature of 800K and Mach number 1.8. The flow field structure of plasma jet，the self-luminosity flame image and flame schlieren were observed by high speed camera. The effects of fuel injection pressure，mixed fuel and plasma jet medium on ignition characteristics were analyzed. Results reveal that the large scale vortex structure form from the shear impact between the plasma jet and airstream. The wake stream of plasma jet is mainly located near the cavity shear layer. The global feature of jet and airstream is mainly expressed at the bow shock induced by jet. The shock wave is strengthened with the jet momentum increases. The combustor steady pressure after ignition increases and the pressure response curve advances with the increase of the fuel injection pressure. There is pressure oscillation and no steady flame with ethylene injection pressure below 0.33MPa. The combustion mode shifts from supersonic combustion to subsonic combustion with ethylene injection pressure ranging from at 0.33MPa to 0.624MPa. The ignition process tends to be steady as ethylene injection pressure above 0.624MPa. The ignition weak limit of ethylene and methane injection pressure is at the 0.394MPa. Though plasma jet provides high temperature working medium，the gas molecules in the wake stream of plasma jet mixed by cold air play a role on the fuel dilution，in turns，it will affect the ignition performance.

Key words: Supersonic combustor；Plasma jet ignition；Fuel injection pressure；Jet medium；Ignition characteristics

刘毅,窦志国,杨波,张鹏. 超声速燃烧室乙烯/空气等离子体射流点火试验研究[J]. 推进技术, 2017, 38(7): 1532-1538.

LIU Yi¹,DOU Zhi-guo¹,YANG BO²,ZHANG Peng¹. Experimental Investigation on Ignition of Ethylene/Air by Plasma Jet in Supersonic Combustor[J]. Journal of Propulsion Technology, 2017, 38(7): 1532-1538.

参考文献

[1] 李钢, 李华, 杨陵元. 俄罗斯等离子体点火和辅助燃烧研究进展[J]. 科技导报, 2012, 30(17): 66-72.
[2] Masuya G, Komuro T, Murakami A. Ignition and Combustion Performance of Scramjet Combustors with Fuel Injection Struts[J]. Journal of Propulsion and Power, 1995, 11(2): 301-307.
[3] 张弯洲, 乐嘉陵, 杨顺华, 等. 马赫数4下氢气自燃辅助乙烯点火实验研究[J]. 推进技术, 2013, 34(12): 1628-1635. (ZHANG Wan-zhou, LE Jia-ling, YANG Shun-hua, et al. Experimental Research on Ethylene Ignition with Hydrogen Self-Ignition Assistant at Mach 4[J]. Journal of Propulsion Technology, 2013, 34(12): 1268-1635.)
[4] Yang V, Li J, Choi J Y. Ignition Transient in an Ethylene Fueled Scramjet Engine with Air Throttling, Part I: Non-Reacting flow Development and Mixing[R]. AIAA 2010-0409.
[5] Yang V, Li J, Choi J Y. Ignition Transient in an Ethylene Fueled Scramjet Engine with Air Throttling, Part II: Ignition and Flame Developmen[R]. AIAA 2010-0410.
[6] 龚诚, 孙明波, 张顺平等. 超声速燃烧室氢气强迫点火过程实验[J]. 推进技术, 2012, 33(4): 547-551. (GONG Cheng, SUN Ming-bo, ZHANG Shun-ping, et al. Experimental Study on the Forced Ignition of Hydrogen in a Supersonic Combustor[J]. Journal of Propulsion Technology, 2012, 33(4): 547-551.)
[7] 韦宝禧, 欧东, 闫明磊, 等. 超燃燃烧室等离子体点火和火焰稳定性能[J]. 北京航空航天大学学报, 2012, 38(12): 1572-1576.
[8] 李飞, 余西龙, 顾洪斌, 等. 超声速气流中煤油射流的等离子体点火实验[J]. 航空动力学报, 2012, 27(4): 824-831.
[9] Hyungrok D, Mark A. Plasma Assisted Cavity Flame Ignition in Supersonic Flows[J]. Combustion and Flame, 157, 2010: 1783-1794.
[10] Kiyotaka S, Ryoichi K. Two-Stage Plasma Torch Ignition in Supersonic Airflows[C]. Salt Lake City: 37th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2001.
[11] Murakami K, Nishikawa A, Takita K. Ignition Characteristics of Hydrocarbon Fuels by Plasma Torch in Supersonic Flow[R]. AIAA 2003-6939.
[12] Kobayashi K, Tomioka S. Ignition by an H2/O₂-Microburner in a Supersonic Air Flow[R]. AIAA 2001-1763.
[13] Kobayashi K, Tomioka S. Supersonic Flow Ignition by Plasma Torch and H2/O₂ Torch[J]. Journal of Propulsion and Power, 2004, 20(2): 294-301.
[14] Masuya G, Takita K, Takahashi K, et al. Effects of Airstream Mach Number on H2/N2 Plasma Igniter[J]. Journal of Propulsion and Power, 2002, 18(3): 679-685.
[15] Do H, Cappelli M A, Mungal M G, et al. Plasma Assisted Cavity Flame Ignition in Supersonic Flow[J]. Combustion and Flame, 2010, 157: 1783-1794.
[16] Stamp G, Ghosh A, Zang A, et al. Experimental Characterization of Acoustic Wave Propagation in a Supersonic Duct[R]. AIAA 2005-4144.　　　　　　　　　　　　　　收稿日期:2016-03-15；修订日期:2016-04-12。作者简介:刘毅,男,硕士生,研究领域为超声速燃烧室等离子体点火助燃技术。E-mail: liuyi19910219@163.com(编辑:田佳莹)