注油方式对超燃冲压发动机燃烧性能的影响
Effect of fueling scheme on scramjet combustion performance
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摘要: 基于脉冲燃烧风洞直连式试验平台,利用壁面压力测量和高速摄影等手段,研究了注油方式对超燃冲压发动机燃烧性能的影响.考察了不同油位单点注油时的注油特性,利用高速摄影揭示了各个油位的火焰发展历程.在产生有效推力及防止进气道不起动的限制下,确定了各个油位的贫油最低当量比、富油最高当量比.研究了第1油位、第2油位和其他油位组合注油时的耦合作用.以隔离段未扰动区域长度、燃烧室内推力、燃料比冲为指标,探寻了燃烧性能最佳的注油方式.试验获得的隔离段未扰动区域长度最大为149.6mm,燃烧室内推力最大为1622.3N,燃料比冲最大为1354.0s.Abstract: Effect of fueling scheme on scramjet combustion performance was investigated based on pulse wind-tunnel direct connected experiment platform. Both pressure measurement and high speed videos were employed.The time evolution of flame with ethylene injected at different single injectors was demonstrated by high speed videos.Under the limits of producing effective thrust and avoiding inlet un-start,the first and second injectors' least and largest fuel equivalence ratios(ER) for combustion were obtained from injecting characteristics experiments.The coupling of the first and second injectors with others was studied.With these initiatory results gained above,different fueling schemes for best combustion performance were investigated under three indexes:isolator undisturbed length,combustor inner thrust and fuel specific impulse.The optimum values for these three indexes were 149.6mm,1622.3N and 1354.0s separately.
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Key words:
- scramjet /
- fueling scheme /
- flame structure /
- flame stabilization mode /
- combustion performance
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[1] Cabell K,Hass N,Storch A,et al.HIFiRE direct-connect rig (HDCR) phase:I scramjet test results from the NASA langley arc-heated scramjet test facility [R].AIAA-2011-2248,2011. [2] XU Jinglei,MA Jing,GU Rui,et al.PIV experimental and numerical investigation of cold flowfield of scramjet combustor with inlet/isolator [R].AIAA-2011-2312,2011. [3] 房田文,丁猛,周进.凹腔超声速流场结构的试验研究[J].国防科技大学学报,2007,29(3):1-5. FANG Tianwen,DINGMeng,ZHOU Jin.Experimental investigation on supersonic flows over cavities[J].Journal of National University of Defense Technology,2007,29(3):1-5.(in Chinese) [4] LI Qing,PAN Yu,TAN Janguo,et al.Experiment research of ramjet with cavity-based flameholder [R].AIAA-2009-5049,2009. [5] Lin K C,Tam C J,Boxx I,et al.Flame characteristics and fuel entrainment inside a cavity flame holder in a scramjet combustor [R].AIAA-2007-5381,2007. [6] Hatakeyama R,Tomioka S,Izumikawa M,et al.Research on combustion of hydrocarbon fuel in a supersonic combustor [R].AIAA-2010-7038,2010. [7] Retaureau G J,Menon S.Experimental studies on flame stability of a fueled cavity in a supersonic crossflow [R].AIAA-2010-6718,2010. [8] Ghodke C D,Pranatharthikarany J,Retaureauz G J,et al.Numerical and experimental studies of flame stability in a cavity stabilized hydrocarbon-fueled scramjet [R].AIAA-2011-2365,2011. [9] SUN Mingbo,WANG Hongbo,BAI Xuesong,et al.Experimental and numerical study on flame stabilization in a supersonic combustor with hydrogen injection upstream of cavity flameholders [R].AIAA-2009-5187,2009. [10] Laurence S J,Schramm J M,Karl S,et al.An experimental investigation of steady and unsteady combustion phenomena in the hyshot:Ⅱ combustor [R].AIAA-2011-2310,2011. [11] Mitani T,Kouchi T.Flame structures and combustion efficiency computed for a Mach 6 scramjet engine[J].Combustion and Flame,2005,142(1):187-196. [12] LI Junhong,SHEN Qing,CHENG Xiaoli,et al.Investigation of equivalence ratio effect on kerosene-fueled low internal drag scramjet combustor performance [R].AIAA-2011-2246,2011. [13] Donbar J M,Linn G J,Srikant S,et al.High-frequency pressure measurements for unstart detection in scramjet isolators [R].AIAA-2010-6557,2010. [14] Micka D J, 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. [15] Heiser W H,Pratt D T,Daley D H, et al.Hypersonic airbreathing propulsion[M].Washington,DC:American Institute of Aeronautics and Astronautics Incorporarion,1994.
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