| 主燃孔轴向位置对低压点火性能的影响 |
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| 引用本文： | 杨谦,林宇震,代威,张弛,王晓峰.主燃孔轴向位置对低压点火性能的影响[J].航空动力学报,2015,30(5):1057-1066. |
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| 作者姓名： | 杨谦 林宇震 代威 张弛 王晓峰 |
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| 作者单位： | 北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室,北京,100191 |
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| 摘 要： | 对回流燃烧室设计了两种主燃孔结构(交错射流和对齐射流),在不同压力条件下对不同主燃孔方案的回流燃烧室的点火性能进行了试验研究.试验结果表明:随着回流燃烧室进口空气压力的降低,点火边界的油气比先减小后升高,而对齐主燃孔的火焰筒方案的低压点火性能优于交错主燃孔.结合火焰筒冷态流场数值模拟和试验中观察到的点火现象进行对比分析,对齐主燃孔方案存在更大范围的回流区,其火焰筒头部参考速度较低.此方案有利于减弱火焰核心的淬熄概率,同时增强头部火焰燃烧的稳定性,从而改善了回流燃烧室的点火性能.
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| 关 键 词： | 主燃孔 轴向位置 回流燃烧室 低压 点火性能 |
| 收稿时间： | 2013/12/6 0:00:00 |
Ignition performance affected by axial position of primary holes at low pressure conditions |
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| YANG Qian,LIN Yu-zhen,DAI Wei,ZHANG Chi and WANG Xiao-feng.Ignition performance affected by axial position of primary holes at low pressure conditions[J].Journal of Aerospace Power,2015,30(5):1057-1066. |
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| Authors: | YANG Qian LIN Yu-zhen DAI Wei ZHANG Chi and WANG Xiao-feng |
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| Institution: | National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China,National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China,National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China,National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China and National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China |
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| Abstract: | Two structures of primary holes (staggered jets and aligned jets) were designed for reverse-flow liner. Experiments were conducted to study the combustor ignition performance affected by two structures of primary holes at different pressure conditions. The experiment result indicates that as the inlet air pressure of the reverse-flow combustor decreases, the fuel/air ratio at ignition boundary decreases at first and then increases. The ignition performance of aligned jets primary holes is better than that of staggered jets primary holes. Combined with numerical simulation results of liner cold flow field and ignition phenomena observed in the experiment, the area of recirculation zone is expanded and reference velocity of the liner is reduced due to the aligned jets primary holes. It is beneficial for decreasing the quenching probability of flame kernel and enhancing the stability of the flame. Thus ignition performance of the reverse-flow combustor is improved. |
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| Keywords: | primary holes axial position reverse-flow combustor low pressure ignition performance |
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