准直流放电等离子体对超燃燃烧室中碳氢燃料燃烧的影响研究 *

推进技术 ›› 2018, Vol. 39 ›› Issue (7): 1556-1561.

准直流放电等离子体对超燃燃烧室中碳氢燃料燃烧的影响研究 *

郑直,聂万胜,车学科,周思引

航天工程大学，北京 101416,航天工程大学，北京 101416,航天工程大学，北京 101416,航天工程大学，北京 101416

发布日期:2021-08-15
基金资助:
国家自然科学基金( 11205244；91441123)。

Effectsof Quasi DCD ischarge Plasmaon Combustionof Hydrocarbon Fuelina Scramjet Combustor

Aerospace Engineering University，Beijing 101416，China,Aerospace Engineering University，Beijing 101416，China,Aerospace Engineering University，Beijing 101416，China and Aerospace Engineering University，Beijing 101416，China

Published:2021-08-15

摘要/Abstract

摘要： 为研究低燃空比条件下，准直流放电等离子对超燃燃烧室中乙烯燃烧流场的影响，在凹腔上游以及底部前壁面处布置电极产生等离子体，通过数值模拟方法，分析了不同等离子体激励强度下，燃烧室凹腔后缘附近压力分布、燃烧室总压损失、乙烯燃烧效率和燃烧室中水的分布情况。研究结果表明:准直流放电等离子体激励强度越高，对凹腔后缘附近压力场稳定能力越强。等离子体的存在，使得燃烧室出口总压损失微弱增加，损失最大值增加 1.9%。燃烧室中乙烯燃烧效率平均提高 1.77倍，随着激励强度的提高，燃烧效率呈现先增高后降低的趋势。等离子体改善了燃烧室中水的分布，凹腔内部产物分布范围更广、燃烧更加充分。

关键词: 超燃冲压发动机；准直流放电；等离子体；数值计算；超声速燃烧

Abstract: To study the effects of quasi-DC discharge plasma on the combustion flow field of ethylene/air in a scramjet combustor under the low equivalent ratio，a quasi-DC discharge plasma filament actuator electrodes crossed upstream of the cavity and bottom of the front wall has been settled. Under the different plasma actuation intensity，the effect of plasma on pressure distribution around the rear wall，the total pressure loss of combustion chamber，the combustion efficiency of ethylene/air and the distribution of water in combustion chamber are nu.merically studied.The results show that，the higher the plasma actuator intensity，the stronger the stability of the pressure field near the rear wall of the cavity. The total pressure loss at the combustor exit slightly increased with the presence of the plasma，the maximum loss increased by 1.9%. The average combustion efficiency of ethylene/air increased by 1.77 times in the combustion chamber，with the increase of the excitation intensity，the combustion efficiency increased first and then decreased. The plasma ameliorates the distribution of water in the combustion chamber，and the water distribution is wider and the combustion is more complete of the interior cavity.

Key words: Scramjet engine； Quasi-DC discharge； Plasma； Mathematical computation； Supersonic combustion

郑直,聂万胜,车学科,周思引. 准直流放电等离子体对超燃燃烧室中碳氢燃料燃烧的影响研究 *[J]. 推进技术, 2018, 39(7): 1556-1561.

ZHENG Zhi,NIE Wan-sheng,CHE Xue-ke,ZHOU Si-yin. Effectsof Quasi DCD ischarge Plasmaon Combustionof Hydrocarbon Fuelina Scramjet Combustor[J]. Journal of Propulsion Technology, 2018, 39(7): 1556-1561.

参考文献

[1] Micka D,Driscoll J F.Combustion Characteristics of a Dual-Mode Scramjet Combustor with Cavity Flameholder[J].Proceedings of the Combustion Institute,2009,32(2): 2397-2404.
[2] Varatharajan B,Williams F A.Ethylene Ignition and Detonation Chemistry,Part 2: Ignition Histories and Re.duced Mechanisms[J]. Journal of Propulsion and Pow. er,2002,18(2): 352-362.
[3] Masuya G,Komuro T,Murakami A,et al.Ignition andCombustion Performance of Scramjet Combustors withFuel Injection Struts[J].Journal of Propulsion and Pow.er,1995,11(2): 301-307.
[4] Busa K M,Rice B,Mcdaniel J C,et al.Scramjet Com.bustion Efficiency Measurement via Tomographic Ab.sorption Spectroscopy and Particle Image Velocimetry[J].AIAA Journal,2016,54(8): 2463-2471.
[5] Kang S H,Lee Y J,Yang S S,et al.Cowl and CavityEffects on Mixing and Combustion in Scramjet Engines[J].Journal of Propulsion and Power,2011,27(6): 1169-1177.
[6] Starikovskiy A,Aleksandrov N L.Plasma-Assisted Ig.nition and Combustion[J].Progress in Energy and Com. bustion Science,2013,39(1): 61-110.
[7] Ju Y,Sun W.Plasma Assisted Combustion: Dynamics and Chemistry[J].Progress in Energy and Combustion Science,2015,48(1): 21-83.
[8] Wagner T C,O'Brien W F,Northam G B,et al.Plasma Torch Igniter for Scramjets[J].Journal of Propulsion and Power,1989,5(5): 548-554.
[9] Masuya G,Takita K,Takahashi K.Effects of Airstream Mach Number on H2 /N2 Plasma Igniter[J].Journal of Propulsion and Power,2002,18(3): 679-685.
[10] Takita K,Shishido K,Kurumada K.Ignition in a Super.sonic Flow by a Plasma Jet of Mixed Feedstock IncludingCH4[J].Proceedings of the Combustion Institute,2011, 33(2): 2383-2389.
[11] Watanabe J,Abe N,Takita K.Effect of a Rearward- Facing Step on Plasma Ignition in Supersonic Flow[J].Journal of Spacecraft & Rockets,2009,46(3): 561-567.
[12] Leonov S B,Yarantsev D A.Mechanisms of Fuel Igni.tion by Electrical Discharge in High-Speed Flow[R].AIAA 2006-7097.
[13] Leonov S B,Yarantsev D A,Gromov V,et al.Mecha. nisms of Flow Control by Near-Surface Electrical Dis.charge Generation[R].AIAA 2005-780.
[14] 段立伟,洪延姬 .等离子体火炬喷射频率对超声速燃烧特性的影响研究[ J].推进技术, 2015,36(10): 1539-1546.(DUAN Li-wei,HONG Yan-ji.Effects ofPlasma Torch Jet Frequency on Supersonic CombustionCharacteristics[J].Journal of Propulsion Technology, 2015,36(10): 1539-1546.)
[15] 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.
[16] 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.
[17] 宋振兴,何立明,张建邦,等 .超音速等离子体点火过程的三维数值模拟[ J].强激光与粒子束, 2012,24 (11): 2746-2750.
[18] Zhou S,Nie W,Che X.Numerical Investigation of In.fluence of Quasi-DC Discharge Plasma on Fuel Jet in Sc.ramjet Combustor[J].IEEE Transactions on Plasma Sci.ence,2015,43(3): 896-905.
[19] 周思引,车学科,聂万胜,等 .等离子体对超燃燃烧室凹腔性能影响的数值研究[ J].推进技术, 2013,34 (7): 950-955.(ZHOU Si-yin,CHE Xue -ke,NIE Wan-sheng,et al.Numerical Study of Effects of Plasmaon Performance of Scramjet Combustor Cavity[J].Jour.nal of Propulsion Technology,2013,34(7): 950-955.)
[20] 郑直,聂万胜,张政,等 .脉冲等离子体对超燃凹腔燃料喷流的影响[ J].红外与激光工程, 2017,46 (2): 37-42.
[21] Roth J R.Aerodynamic Flow Acceleration Using Para.electric and Peristaltic Electrohydrodynamic Effects of aOne Atmosphere Uniform Glow Discharge Plasma[J].Physics of Plasmas,2003,10(5): 2117-2126.
[22] Leonov S B,Yarantsev D.Near-Surface Electrical Dis. charge in Supersonic Airflow: Properties and Flow Con.trol[J].Journal of Propulsion and Power,2008,24(6): 1168-1181.
[23] 秦曾衍,左公宁,王永荣,等 .高压强脉冲放电及其应用[ M].北京:北京工业大学出版社, 2000: 352-355.
[24] Rajasekaran A,Babu V.Numerical Simulation of Three Dimensional Reacting Flow in a Model Supersonic Com.bustor[J].Journal of Propulsion and Power,2004,22 (4): 820-827.
[25] Baurle R,Mathur T,Gruber M,et al.A Numerical and Experimental Investigation of a Scramjet Combustor forHypersonic Missile Applications[C].USA: 34th AIAA / ASME/SAE/ASEE Joint Propulsion Conference and Exhib.it Cleveland,1998.
[26] 周思引 .超燃冲压发动机等离子体助燃 /稳燃研究[D].北京:装备学院, 2014.(编辑:张荣莉) * 收稿日期: 2017-06-30；修订日期: 2017-08-26。基金项目:国家自然科学基金( 11205244；91441123)。通讯作者:郑直,男,博士生,研究领域为等离子体助燃技术。 E-mail: dymzz1166@163.com