介质阻挡等离子体对航空发动机燃烧室特性的影响
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摘要
建立了航空发动机燃烧室等离子体助燃实验平台,开展了航空发动机燃烧室DBD(dielectric barrier discharge)等离子体助燃在模拟航空发动机燃烧室最大状态条件下的性能实验。通过正常燃烧和等离子体助燃的对比实验和分析,研究了等离子体助燃对4种余气系数和5种电压条件下的平均出口温度、燃烧效率、出口不均匀系数的影响。实验结果表明,与正常工况相比,等离子体助燃后的燃烧效率有所提高,当电压为40 kV时,等离子体助燃时的燃烧效率在富燃料条件下提高了2.31%。实施助燃后出口温度场均匀性也得到改善,但在富油条件下效果最好,出口温度分布系数的减小量超过5%。这些结果对未来将等离子体助燃技术应用于航空发动机燃烧室并提高其性能具有一定的参考价值。
A test platform was developed to investigate the performance of aero-engine combustor by the dielectric barrier discharge(DBD) plasma assisted combustion(PAC) in the simulated maximum condition. Conventional combustion experiments and plasma-assisted combustion conditions were conducted to study the effect of PAC on the performances including average outlet temperature, combustion efficiency and pattern factor under four different excessive air coefficients five different voltages. The comparative experiment shows that the combustion efficiency is improved after PAC compared with the normal conditions, the combustion efficiency of PAC increases 2.31% in the fuel-rich condition when Up-p is 40 kV. The uniformity of the outlet temperature field is also improved after PAC, the decrease of the pattern factor is more than 5% in the fuel-rich condition. These results offer certain reference value for the future application of PAC in aero-engine combustor and improving its performance.
A test platform was developed to investigate the performance of aero-engine combustor by the dielectric barrier discharge(DBD) plasma assisted combustion(PAC) in the simulated maximum condition. Conventional combustion experiments and plasma-assisted combustion conditions were conducted to study the effect of PAC on the performances including average outlet temperature, combustion efficiency and pattern factor under four different excessive air coefficients five different voltages. The comparative experiment shows that the combustion efficiency is improved after PAC compared with the normal conditions, the combustion efficiency of PAC increases 2.31% in the fuel-rich condition when Up-p is 40 kV. The uniformity of the outlet temperature field is also improved after PAC, the decrease of the pattern factor is more than 5% in the fuel-rich condition. These results offer certain reference value for the future application of PAC in aero-engine combustor and improving its performance.
引文
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[24] NEMMICH S,TILMATINE A,DEY Z,et al.Optimal Sizing of a DBD Ozone Generator Using Response Surface Modeling[J].Ozone:Science & Engineering,2015,32:3-8
[25] BURIKO Y,VINOGRADOV V,GOLTSEV V,et al.Influence of Active Radical Concentration on Self-ignition Delay of a Propane/Air Mixture[C]//37th Joint Propulsion Conference and Exhibit,2001
[26] STARIKOVSKAIA S M,KOSAREV L N,KRASNOCHUB A V,et al.Control of Combustion and Ignition of Hydrocarbon Containing Mixtures by Nanosecond Pulsed Discharges[C]//43th AIAA Aerospace Sciences Meeting and Exhibit,2005
[27] DING Guoyu,HE Xiaomin,ZHAO Ziqiang,et al.Effect of Dilution Holes on the Performance of a Triple Swirler Combustor[J].Chinese Journal of Aeronautics,2014,27(6):61421-1429
[2] STARIKOVSKAIA S M.Plasma Assisted Ignition and Combustion[J].Journal of Physics D:Applied Physics,2006,39(19):265-299
[3] JU Yiguang,SUN Wenting.Plasma Assisted Combustion:Dynamics and Chemistry[J].Progress in Energy and Combustion Science,2013,48:21-83
[4] KLIMOV A,BITIURIN V,MORALEV I,et al.Non-Premixed Plasma Assisted Combustion of Hydrocarbon Fuel in High-speed Airflow[C]//44th AIAA Aerospace Sciences Meeting and Exhibit,2006
[5] KIM W,DO H,MUNGAL M G,et al.Flame Stabilization Enhancement and NOx Production Using Ultra Short Repetitively Pulsed Plasma Discharges[C]//44th AIAA Aerospace Sciences Meeting and Exhibit,2006
[6] 兰宇丹,何立明,郭向阳,等.不同初始温度下等离子体对H2/Air 混合物燃烧影响[J].推进技术,2009,30(6):651-655LAN Yudan,HE Liming,GUO Xiangyang,et al.Effects of Plasma on the Combustion of H2/Air Mixture under Different Initial Temperatures[J].Journal of Propulsion and Technology,2009,30(6):651-655.(in Chinese)
[7] 胡宏斌,徐纲,房爱兵,等.非平衡等离子体助燃低热值气体燃料[J].工程热物理学报,2010,31(9):1603-1606HU Hongbin,XU Gang,FANG Aibing,et al.Non-Equilbrium Plasma Assisted Combustion of Low Fuels[J].Journal of Engineering Thermophysics,2010,31(9):1603-1606 (in Chinese)
[8] 穆海宝,喻琳,李平,等.CH4/O2/He 混合气体作大气压介质阻挡放电处理后其燃烧特性的改变[J].高电压技术,2014,40(10):2980-2985MU Haibao,YU Lin,LI Ping,et al.Enhancement of the Premixed CH4/O2/He Flame Speed with Dielectric Barrier Discharge[J].High Voltage Engineering,2014,40(10):2980-2985 (in Chinese)
[9] HICKS A,NORBERG S,SHAWCROSS P,et al.Singlet Oxygen Generation in a High Pressure Non-Self-Sustained Electric Discharge[J].Journal of Physics D:Applied Physics,2005,38(20):3812-3824
[10] CATHEY C D,TANG TAO,SHIRAISHI T,et al.Nanosecond Plasma Ignition for Improved Performance of an Internal Combustion Engine[J].IEEE Trans on Plasma Science,2007,35(6):1664-1668
[11] HWANG J,BAE C,PARK J,et al.Microwave-Assisted Plasma Ignition in a Constant Volume Combustion Chamber[J].Combustion and Flame,2016,167:86-96
[12] MATVEEV I,MATVEEVA S,GUTSOL A,et al.Non-Equilibrium Plasma Igniters and Pilots for Aerospace Application[C]//43rd AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition,2005
[13] FRIDMAN A,CHIROKOV A,GUTSOL A.Non-thermal Atmospheric Pressure Discharges[J].Journal of Physics D:Applied Physics,2005,38(2):R1-R24
[14] LIU Xingjian,HE Liming,YU Jinlu,et al.Experimental Investigation of Effects of Airflows on Plasma-assisted Combustion Actuator Characteristics [J].Journal of Physics D:Applied Physics,2015,24(4):6
[15] 宋振兴,丁未,刘兴建,等.空气放电等离子体助燃激励器的动力学机理[J].高电压技术,2014,40(7):2095-2100SONG Zhenxing,DING Wei,LIU Xingjian,et al.Kinetic Mechanism of Air Discharge Plasma Assisted Combustion Actuator[J].High Voltage Engineering,2014,40(7):2095-2100 (in Chinese)
[16] YANG Suo,NAGARAJA S,SUN Wenting,et al.Multiscale Modeling and General Theory of Non-Equilibrium Plasma-Assisted Ignition and Combustion [J].Journal of Physics D:Applied Physics,2017,50:18
[17] 何立明,雷健平,陈一,等.大气压交流旋转滑动弧的放电特性[J].高电压技术,2017,43(9):3061-3069HE Liming,LEI Jianping,CHEN Yi,et al.Characteristic of Atmospheric Pressure AC Rotating Gliding Arc Discharge[J].High Voltage Engineering,2017,43(9):3061-3069 (in Chinese)
[18] 赵明龙,杨志民,林宇震,等.单头部/扇形/全环燃烧室贫油点火性能换算[J].航空动力学报,2013,32(8):1822-1826ZHAO Minglong,YANG Zhimin,LIN Yuzhen,et al.Conversion Methods for Lean Ignition Performances among Single-Sector,Multi-Sector and Full Annular Combustors[J].Journal of Aerospace Power,2013,32(8):1822-1826 (in Chinese)
[19] OMBRELLO T,WON S H,JU Yiguang,et al.Flame Propagation Enhancement by Plasma Excitation of Oxygen.Part I:Effects of O3 [J].Combustion and Flame,2010,157(10):1906-1915
[20] 宋振兴,丁未,刘兴建,等.空气放电等离子体助燃激励器的动力学机理[J].高电压技术,2014,40(7):2095-2100SONG Zhenxing,DING Wei,LIU Xingjian,et al.Kinetic Mechanism of Air Discharge Plasma Assisted Combustion Actuator[J].High Voltage Engineering,2014,40(7):2095-2100 (in Chinese)
[21] 黎明,吴二平,索建秦,等.某型燃烧室火焰筒的性能对比试验[J].航空动力学报,2013,28(8):1689-1695LI Ming,WU Erping,SUO Jianqin,et al.Performance Comparative Experiment on Flame Tubes of a Certain Combustor[J].Journal of Aerospace Power,2013,28(8):1689-1695 (in Chinese)
[22] 张宝诚.航空发动机试验和测试技术[M].北京:北京航空航天大学出版社,2005ZHANG Baocheng.Aero-Engine Test and Testing Technology[M].Beijing,Beijing University of Aeronautics and Astronautics Press,2005 (in Chinese)
[23] BOONDUANG S,LIMSUWAN S,KONGSRI W,et al.Effect of Oxygen Pressure and Flow Rate on Electrical Characteristic and Ozone Concentration of a Cylinder-cylinder DBD Ozone Generator[J].Procedia Engineering,2012,32:936-942
[24] NEMMICH S,TILMATINE A,DEY Z,et al.Optimal Sizing of a DBD Ozone Generator Using Response Surface Modeling[J].Ozone:Science & Engineering,2015,32:3-8
[25] BURIKO Y,VINOGRADOV V,GOLTSEV V,et al.Influence of Active Radical Concentration on Self-ignition Delay of a Propane/Air Mixture[C]//37th Joint Propulsion Conference and Exhibit,2001
[26] STARIKOVSKAIA S M,KOSAREV L N,KRASNOCHUB A V,et al.Control of Combustion and Ignition of Hydrocarbon Containing Mixtures by Nanosecond Pulsed Discharges[C]//43th AIAA Aerospace Sciences Meeting and Exhibit,2005
[27] DING Guoyu,HE Xiaomin,ZHAO Ziqiang,et al.Effect of Dilution Holes on the Performance of a Triple Swirler Combustor[J].Chinese Journal of Aeronautics,2014,27(6):61421-1429