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| 注油方式对超燃冲压发动机燃烧性能的影响 | |
| 引用本文： | 邓维鑫,乐嘉陵,杨顺华,田野,张弯洲,许明恒.注油方式对超燃冲压发动机燃烧性能的影响[J].航空动力学报,2013,28(7):1449-1457. |
| 作者姓名： | 邓维鑫 乐嘉陵 杨顺华 田野 张弯洲 许明恒 |
| 作者单位： | 1. 西南交通大学 机械工程学院,成都610031;中国空气动力研究与发展中心吸气式高超声速研究中心,四川 绵阳621000 2. 中国空气动力研究与发展中心吸气式高超声速研究中心,四川 绵阳,621000 3. 西南交通大学 机械工程学院,成都,610031 |
| 基金项目： | 国家自然科学青年科学基金(10902109) |
| 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1 354.0s. |
| 关 键 词： | 超燃冲压发动机 注油方式 火焰结构 稳焰模式 燃烧性能 |
| 收稿时间： | 2012/11/26 0:00:00 |
Effect of fueling scheme on scramjet combustion performance |
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| DENG Wei-xin,LE Jia-ling,YANG Shun-hu,TIAN Ye,ZHANG Wan-zhou and XU Ming-heng.Effect of fueling scheme on scramjet combustion performance[J].Journal of Aerospace Power,2013,28(7):1449-1457. | |
| Authors: | DENG Wei-xin LE Jia-ling YANG Shun-hu TIAN Ye ZHANG Wan-zhou and XU Ming-heng |
| Institution: | School of Mechanical Engineering, Southwest Jiaotong University, Chengdu 610031, China;Air-breathing Hypersonic Technology Research Center, China Aerodynamics Research and Development Center, Mianyang Sichuan 629000, China;Air-breathing Hypersonic Technology Research Center, China Aerodynamics Research and Development Center, Mianyang Sichuan 629000, China;Air-breathing Hypersonic Technology Research Center, China Aerodynamics Research and Development Center, Mianyang Sichuan 629000, China;Air-breathing Hypersonic Technology Research Center, China Aerodynamics Research and Development Center, Mianyang Sichuan 629000, China;School of Mechanical Engineering, Southwest Jiaotong University, Chengdu 610031, China;Air-breathing Hypersonic Technology Research Center, China Aerodynamics Research and Development Center, Mianyang Sichuan 629000, China;School of Mechanical Engineering, Southwest Jiaotong University, Chengdu 610031, China |
| 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. |
| Keywords: | scramjet fueling scheme flame structure flame stabilization mode combustion performance |
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