凹腔底壁喷注煤油燃料的超燃点火试验
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摘要
在来流总温为1 486K、总压为1.6MPa、马赫数为2.52的条件下,采用两级串联凹腔构型燃烧室,开展了凹腔底壁喷注煤油燃料的超燃点火试验,研究了喷嘴孔径、喷注位置对点火性能的影响.结果表明:上游凹腔底壁大孔径喷嘴喷注燃料,下游凹腔点火的方案点火性能高,在煤油总体当量比为0.102~0.206范围内均可实现成功点火与稳定燃烧;燃烧反压向上游的传播过程具有明显的滞后性且与分离区的形成过程紧密耦合;燃料喷注方案决定了煤油雾化燃料场的分布,燃料的分布特征又决定了点火特征.
Experiment on ignition of kerosene injected from cavity floor in scramjet combustor with two-staged cavities were conducted at the inflow conditions of Mach number of2.52,total temperature of 1 486 K,total pressure of 1.6MPa.The influences of injector diameter and injection position on ignition ability were analyzed.Results showed that when kerosene was injected from the upstream cavity floor using large diameter injector and ignited by the spark in the downstream cavity,it led to a reliable ignition with large margin of flame stability(kerosene overall equivalent ratio range of 0.102-0.206).The upstream propagation of pressure disturbance had an obvious hysteresis phenomenon and interacted with the formation of separating zone.The kerosene spray distribution was governed by the fuel injection scheme,and influenced the ignition characteristics on the other hand.
Experiment on ignition of kerosene injected from cavity floor in scramjet combustor with two-staged cavities were conducted at the inflow conditions of Mach number of2.52,total temperature of 1 486 K,total pressure of 1.6MPa.The influences of injector diameter and injection position on ignition ability were analyzed.Results showed that when kerosene was injected from the upstream cavity floor using large diameter injector and ignited by the spark in the downstream cavity,it led to a reliable ignition with large margin of flame stability(kerosene overall equivalent ratio range of 0.102-0.206).The upstream propagation of pressure disturbance had an obvious hysteresis phenomenon and interacted with the formation of separating zone.The kerosene spray distribution was governed by the fuel injection scheme,and influenced the ignition characteristics on the other hand.
引文
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[3]丁猛,余勇,梁剑寒,等.碳氢燃料超燃冲压发动机点火技术试验[J].推进技术,2004,25(6):566-569.DING Meng,YU Yong,LIANG Jianhan,et al.Experimental investigation of ignition technology in liquid hydrocarbon fueled scramjet combustor[J].Journal of Propulsion Technology,2004,25(6):566-569.(in Chinese)
[4]YU Gang,LI Jianguo,ZHANG Xinyu,et al.Investigation on combustion characteristics of kerosene-hydrogen dual fuel in a supersonic combustor[R].AIAA-2000-3620,2000.
[5]PAN Yu,LIU Weidong,WANG Zhenguo.Cavities installation schemes affect on the scramjet ignition[R].AIAA-2007-5400,2007.
[6]Yu G,Li J G,Zhao J R,et al.An experimental study of kerosene combustion in a supersonic model combustor using effervescent atomization[J].Proceedings of the Combustion Institute,2005,30(2):2859-2866.
[7]王辽,章成亮,韦宝禧,等.应用气泡雾化喷嘴的煤油超声速燃烧试验[J].航空动力学报,2009,24(2):353-359.WANG Liao,ZHANG Chengliang,WEI Baoxi,et al.Experimental investigation of kerosene supersonic combustion test using aerated-liquid injectors[J].Journal of Aerospace Power,2009,24(2):353-359.(in Chinese)
[8]HU Jichao,BAO Wen,CHANG Juntao.Flame transition in dual-mode scramjet combustor with oxygen piloted ignition[J].Journal of Propulsion and Power,2014,30(4):1103-1107.
[9]Situ M,Wang C,Lu H P,et al.Hot gas piloted energy for supersonic combustion of kerosene with dual-cavity[R].AIAA-2001-0523,2001.
[10]Situ M,Wang C,Zhuang F G,et al.Investigation of supersonic combustion of kerosene jets with hot gas piloted energy and dual-cavity[R].AIAA-2002-0804,2002.
[11]席文雄,王振国,李庆,等.超声速气流中煤油喷雾的热射流强迫点火[J].航空动力学报,2012,27(11):2436-2441.XI Wenxiong,WANG Zhenguo,LI Qing,et al.Forcedignition of kerosene spray in supersonic airflow with hot gas injection[J].Journal of Aerospace Power,2012,27(11):2436-2441.(in Chinese)
[12]XI Wenxiong,WANG Zhenguo,SUN Mingbo,et al.Experimental investigation of ignition transient phase in model supersonic combustor[J].Journal of Aerospace Engineering,2014,27(4):1-9.
[13]LI Qing,XI Wenxiong,LAI Lin,et al.Research on hot gas jet ignition process of scramjet combustor fueled with kerosene[R].AIAA-2012-5947,2012.
[14]宋文艳,刘伟雄,贺伟,等.超声速燃烧室等离子体点火实验研究[J].实验流体力学,2006,20(4):20-24.SONG Wenyan,LIU Weixiong,HE Wei,et al.Experimental investigation of plasma ignition in supersonic combustor[J].Journal of Experiments in Fluid Mechanics,2006,20(4):20-24.(in Chinese)
[15]Timothy C W,Walter F O B,Northam G B.Plasma torch igniter for scramjets[J].Journal of Propulsion and Power,1989,5(5):548-554.
[16]李西鹏.超声速气流中煤油燃料火花塞直接点火过程研究[D].长沙:国防科学技术大学,2014.LI Xipeng.Investigation on spark ignition process of kerosene in supersonic flow[D].Changsha:National University of Defense Technology,2014.(in Chinese)
[17]Lin K C,Jackson K,Behdadnia R,et al.Acoustic characterization of an ethylene-fueled scramjet combustor with a cavity flameholder[J].Journal of Propusion and Power,2010,26(6):1161-1169.
[18]Kouchi T,Masuya G,Mitani T,et al.Mechanism and control of combustion-mode transition in a scramjet engine[J].Journal of Propusion and Power,2012,28(1):106-112.