微波增强滑移电弧等离子体辅助超声速燃烧

doi:10.7527/S1000-6893.2019.23345

流体力学与飞行力学

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微波增强滑移电弧等离子体辅助超声速燃烧

孟宇^1,2, 顾洪斌², 孙文明^1,2, 张新宇^1,2

1. 中国科学院大学工程科学学院, 北京 100049;
2. 中国科学院力学研究所高温气体动力学国家重点实验室, 北京 100190

收稿日期:2019-08-06 修回日期:2019-08-27 出版日期:2020-02-15 发布日期:2019-10-17
通讯作者: 顾洪斌 E-mail:guhb@imech.ac.cn
基金资助:
国家自然科学基金（11772342）

Microwave enhanced gliding arc plasma assisted supersonic combustion

MENG Yu^1,2, GU Hongbin², SUN Wenming^1,2, ZHANG Xinyu^1,2

1. School of Engineering Science, University of Chinese Academy of Sciences, Beijing 100049, China;
2. The State Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China

Received:2019-08-06 Revised:2019-08-27 Online:2020-02-15 Published:2019-10-17
Supported by:
National Natural Science Foundation of China (11772342)

摘要/Abstract

摘要： 为了研究微波增强滑移电弧等离子体对超声速燃烧火焰结构的影响，在超燃冲压发动机直连式实验台发动机模型加装了微波和滑移电弧结构，进行了超声速稳定燃烧实验。以单级凹腔作为火焰稳定器，燃烧室来流马赫数为2.5，常温乙烯从壁面横向射流，燃料射流点之前放置滑移电弧电极，凹腔对侧馈入2.45 GHz的微波。研究表明，在超燃冲压发动机燃烧室内滑移电弧同样遵循放电和扩展的周期特性，由于气流流速极高，滑移电弧周期约达125 kHz。等离子体的加入使燃烧室预燃激波串前移，火焰的起始和稳定位置从凹腔剪切层向燃料射流前部转移，超声速火焰燃烧速率提高。与单一的微波或滑移电弧等离子体增强燃烧方法相比，微波与滑移电弧的结合可在较低的能耗下，实现与高功率微波等效的效果。微波增强滑移电弧等离子体能够对超声速燃烧起到稳定作用。

关键词: 超燃冲压发动机, 超声速燃烧, 等离子体助燃, 滑移电弧, 微波

Abstract: To study the effect of microwave enhanced gliding arc plasma on supersonic combustion, an experiment is carried out on a direct-connected scramjet facility that has installed microwave and gliding arc structures. A single-stage cavity is used as flame stabilizer. The inlet Mach number of combustor is 2.5. The room temperature ethylene is injected perpendicular from the combustor wall, the gliding arc electrode is set in front of fuel jet point, and 2.45 GHz microwave is fed into scramjet in the opposite side of the cavity. The results show that the gliding arc in the scramjet combustor also follows the periodic characteristics of discharge and expansion. Due to the extremely high airflow rate, the gliding arc period is approximately 125 kHz. The plasma causes the pre-combustion shock train of the combustor to move forward, and the initial and stable position of the flame is transferred from the cavity shear layer to the front of the fuel jet, and the supersonic flame rate is increased. Compared with a single microwave or the gliding arc plasma method, the combination of microwave and gliding arc can achieve high power microwave equivalent effect at a lower energy consumption. The study concludes that the microwave enhanced gliding arc plasma can stabilize the supersonic combustion.

Key words: scramjet, supersonic combustion, plasma assisted combustion, gliding arc, microwave

中图分类号:

V434⁺.3

孟宇, 顾洪斌, 孙文明, 张新宇. 微波增强滑移电弧等离子体辅助超声速燃烧[J]. 航空学报, 2020, 41(2): 123345-123345.

MENG Yu, GU Hongbin, SUN Wenming, ZHANG Xinyu. Microwave enhanced gliding arc plasma assisted supersonic combustion[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(2): 123345-123345.

参考文献 28

[1]	BILLIG F S. Research on supersonic combustion[J]. Journal of Propulsion and Power, 1993, 9(4):499-514.
[2]	JU Y G, SUN W T. Plasma assisted combustion:Dynamics and chemistry[J]. Progress in Energy and Combustion Science, 2015, 48:21-83.
[3]	DOOLEY S, WON S H, HEYNE J, et al. The experimental evaluation of a methodology for surrogate fuel formulation to emulate gas phase combustion kinetic phenomena[J]. Combustion and Flame, 2012, 159(4):1444-1466.
[4]	ZHU S H, XU X, JI P F. Flame stabilization and propagation in dual-mode scramjet with staged-strut injectors[J]. AIAA Journal, 2017, 55(1):171-179.
[5]	ZHANG Y, ZHU S H, CHEN B, et al. Hysteresis of mode transition in a dual-struts based scramjet[J]. Acta Astronautica, 2016, 128:147-159.
[6]	ZHU S H, XU X, YANG Q C, et al. Intermittent back-flash phenomenon of supersonic combustion in the staged-strut scramjet engine[J]. Aerospace Science and Technology, 2018, 79:70-74.
[7]	ZHANG J L, CHANG J T, MA J C, et al. Investigation of flame establishment and stabilization mechanism in a kerosene fueled supersonic combustor equipped with a thin strut[J]. Aerospace Science and Technology, 2017, 70:152-160.
[8]	MASUMOTO R, TOMIOKA S, KUDO K, et al. Experimental study on combustion modes in a supersonic combustor[J]. Journal of Propulsion and Power, 2011, 27(2):346-355.
[9]	JU Y G, SUN W T. Plasma assisted combustion:Progress, challenges, and opportunities[J]. Combustion and Flame, 2015, 162(3):529-532.
[10]	LI F, YU X L, TONG Y G, et al. Plasma-assisted ignition for a kerosene fueled scramjet at Mach 1.8[J]. Aerospace Science and Technology, 2013, 28(1):72-78.
[11]	CAI Z, ZHU J J, SUN M B, et al. Spark-enhanced ignition and flame stabilization in an ethylene-fueled scramjet combustor with a rear-wall-expansion geometry[J]. Experimental Thermal and Fluid Science, 2018, 92:306-313.
[12]	FENG R, LI J, WU Y, et al. Experimental investigation on gliding arc discharge plasma ignition and flame stabilization in scramjet combustor[J]. Aerospace Science and Technology, 2018, 79:145-153.
[13]	LI X H, YANG L C, PENG J B, et al. Cavity ignition of liquid kerosene in supersonic flow with a laser-induced plasma[J]. Optics Express, 2016, 24(22):25362.
[14]	AN B, WANG Z G, YANG L C, et al. Experimental investigation on the impacts of ignition energy and position on ignition processes in supersonic flows by laser induced plasma[J]. Acta Astronautica, 2017, 137:444-449.
[15]	KHODATAEV K V. Microwave discharges and possible applications in aerospace technologies[J]. Journal of Propulsion and Power, 2008, 24(5):962-972.
[16]	BAUROV A Y, SHIBKOVA L V, SHIBKOV V M, et al. External combustion of high-speed multicomponent hydrocarbon-air flow under conditions of low-temperature plasma[J]. Moscow University Physics Bulletin, 2013, 68(4):293-298.
[17]	SHIBKOV V M, SHIBKOVA L V, KARACHEV A A, et al. The spatial-temporal evolution of combustion under conditions of low temperature discharge plasma of liquid alcohol injected into an air stream[J]. Moscow University Physics Bulletin, 2012, 67(1):138-142.
[18]	SHIBKOV V M, SHIBKOVA L V, GROMOV V G, et al. Influence of surface microwave discharge on ignition of high-speed propane-air flows[J]. High Temperature, 2011, 49(2):155-167.
[19]	SHIBKOV V M, SHIBKOVA L V. Parameters of the flame due to surface-microwave discharge-initiated inflammation of thin alcohol films[J]. Technical Physics, 2010, 55(1):58-65.
[20]	BABUSHOK V I, DELUCIA F C, GOTTFRIED J L, et al. Double pulse laser ablation and plasma:Laser induced breakdown spectroscopy signal enhancement[J]. Spectrochimica Acta Part B:Atomic Spectroscopy, 2006, 61(9):999-1014.
[21]	MICHAEL J B, DOGARIU A, SHNEIDER M N, et al. Subcritical microwave coupling to femtosecond and picosecond laser ionization for localized, multipoint ignition of methane/air mixtures[J]. Journal of Applied Physics, 2010, 108(9):093308.
[22]	WOLK B, DEFILIPPO A, CHEN J Y, et al. Enhancement of flame development by microwave-assisted spark ignition in constant volume combustion chamber[J]. Combustion and Flame, 2013, 160(7):1225-1234.
[23]	IKEDA Y, NISHIYAMA A, KANEKO M. Microwave enhanced ignition process for fuel mixture at elevated pressure of 1 MPa:AIAA-2009-0223[R]. Reston, VA:AIAA, 2009.
[24]	ELSABBAGH M, KADO S, IKEDA Y, et al. Measurements of rotational temperature and density of molecular nitrogen in spark-plug assisted atmospheric-pressure microwave discharges by rotational Raman scattering[J]. Japanese Journal of Applied Physics, 2011, 50(7):076101.
[25]	FRIDMAN A, NESTER S, KENNEDY L A, et al. Gliding arc gas discharge[J]. Progress in Energy and Combustion Science, 1999, 25(2):211-231.
[26]	孟宇,顾洪斌,张新宇. 微波对超声速燃烧火焰结构的影响[J]. 航空学报, 2019, 40(12):123224. MENG Y, GU H B, ZHANG X Y. Influence of microwave on structure of supersonic combustion flame[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(12):123224(in Chinese).
[27]	WANG Z P, GU H B, CHENG L W, et al. CH* luminance distribution application and a one-dimensional model of the supersonic combustor heat release quantization[J]. International Journal of Turbo & Jet-Engines, 2019, 36(1):45-50.
[28]	RAO X, HEMAWAN K, WICHMAN I, et al. Combustion dynamics for energetically enhanced flames using direct microwave energy coupling[J]. Proceedings of the Combustion Institute, 2011, 33(2):3233-3240.

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微波增强滑移电弧等离子体辅助超声速燃烧

Microwave enhanced gliding arc plasma assisted supersonic combustion

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