多级旋流预燃区补氧对常压点火特性的影响

王柏森; 张弛; 林宇震; 姜文彬

多级旋流预燃区补氧对常压点火特性的影响

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

详细信息

作者简介:
王柏森（1989- ），男，山东烟台人，硕士生，主要从事航空发动机燃烧室研究.

中图分类号: V23
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出版历程
- 收稿日期: 2013-09-08
- 刊出日期: 2014-05-28

Influence of oxygen addition in multi-swirl pilot zone on atmospheric pressure ignition characteristics

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

摘要

摘要: 在常温常压进口条件下开展点火试验，研究对象为多级旋流空气雾化喷嘴模型燃烧室，在火焰筒压降为1%~6%工况下分别采用20J和12J点火能量的电火花点火器进行点火试验，控制预燃区补氧空气流量比在0~0.04范围内，研究了多级旋流空气雾化喷嘴的点火油气比变化规律.结果表明：在点火油气比足够小的情况下，预燃区补氧流量越高，临界进口速度越大；在相同点火能量和火焰筒压降下，预燃区补氧空气流量比越高，点火油气比越小；随着预燃区补氧空气流量比增大到一个阈值（20J点火能量时为0.01，12J点火能量时为0.015），点火油气比曲线的发展趋势将发生变化；当预燃区补氧空气流量比继续增大到另一个关键阈值（20J点火能量时为0.025，12J点火能量时为0.03），点火油气比不再发生明显改变.
- 燃烧室 /
- 点火 /
- 多级旋流 /
- 预燃区 /
- 补氧 /
- 临界进口速度 /
- 油气比
Abstract: The ignition experiments were conducted on atmospheric pressure and normal temperature. The experimental research object was a model combustor with multi-swirl air atomizing nozzle. The systematic parameters for study consist of atmospheric pressure, normal temperature, pressure drop of chamber of 1%-6%, ignition energy of 20J and 12J, mass flow ratios of oxygen and air in pilot zone of 0-0.04. The change rule of ignition fuel-air ratio of multi-swirl air atomizing nozzle. The results indicate that when ignition fuel-air ratio is small enough, maximum ignition air flow velocity at combustor inlet increases with the rising oxygen addition mass flow in pilot zone. On the condition of the same ignition energy and pressure drop of chamber, while the mass flow ratio of oxygen and air in pilot zone increases, the ignition fuel-air ratio reduces. When the mass flow ratio of oxygen and air in pilot zone increases to a threshold value (20J-0.01, 12J-0.015), the trend of ignition fuel-air ratio of curve changes. When it continues rising to another threshold value (20J-0.025, 12J-0.03), the ignition fuel-air ratio will not change.
- combustor /
- ignition /
- multi-swirl /
- pilot zone /
- oxygen addition /
- maximum ignition air flow velocity at combustor inlet /
- fuel-air ratio

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参考文献(18)

[1]	林宇震, 许全宏, 刘高恩.燃气轮机燃烧室[M].北京:国防工业出版社, 2008.
[2]	Caines B N, Hicks R A, Wilson C W.Influence of sub-atmospheric conditions on the performance of an airblast atomiser[R].AIAA-2001-3573, 2001.
[3]	Lefebvre A H.Gas turbine combustion[M].2nd ed.Philadelphia:Taylor and Francis, 1999.
[4]	陈能坤, 周雁.燃油增温对高空低压点火性能影响的实验研究[J].推进技术, 1996, 17(6):69-72. CHEN Nengkun, ZHOU Yan.Effect of advanced fuel temperature on the high altitude ignition performance[J].Journal of Propulsion Technology, 1996, 17(6):69-72.(in Chinese)
[5]	Chen N K, Zhao Y H, Wu S S, et al.Effect of oxygen addition on ignition of aero-gas turbine at simulated altitude facility[J].Journal of Energy, 1982, 6(6):425-429.
[6]	Liu C Y, Chen G, Sipcz N, et al.Characteristics of oxy-fuel combustion in gas turbines[J].Applied Energy, 2012, 89(1):387-394.
[7]	Chin J S.Analysis of the effect of oxygen addition on minimum ignition energy[R].AIAA 82-1160, 1982.
[8]	Kutne P, Kapadia B K, Meier W, et al.Experimental analysis of the combustion behaviour of oxyfuel flames in a gas turbine model combustor[J].Proceedings of the Combustion Institute, 2011, 33(2):3383-3390.
[9]	Ardha V R, Dam B, Love N, et al.Characterization of oxy-fuel flames in a swirl based combustor[R].AIAA-2012-3786, 2012.
[10]	Keating E L, Gupta A K.Effects of oxygen enrichment on the predicted indicated performance of an IC engine[R].AIAA 94-3826-CP, 1994.
[11]	Werle S, Wilk R K.Ignition of methane and propane in high-temperature oxidizers with various oxygen concentrations[J].Fuel, 2010, 89(8):1833-1839.
[12]	王玉峰, 段小龙.冲压发动机点火前内流场数值仿真研究[J].火箭推进, 2006, 32(6):20-22. WANG Yufeng, DUAN Xiaolong.Numerical study of the ramjet engine inner flow before ignition[J].Journal of Rocket Propulsion, 2006, 32(6):20-22.(in Chinese)
[13]	薛鑫, 林宇震, 张弛.火焰筒压力损失对点火特性的影响[J].航空动力学报, 2012, 27(10):2229-2235. XUE Xin, LIN Yuzhen, ZHANG Chi.Effects of liner pressure loss on combustor ignition performances[J].Journal of Aerospace Power, 2012, 27(10):2229-2235.(in Chinese)
[14]	Gupta A K.Effect of swirl and flow distribution on the spray flame characteristics.Las Vegas:Energy Conversion Engineering Conference and Exhibit, 2000.
[15]	Dagaut P, Cathonnet M.The ignition, oxidation, and combustion of kerosene:a review of experimental and kinetic modeling[J].Progress in Energy and Combustion Science, 2006, 32(1):48-92.
[16]	Gupta A K, Damm T, Charagundla S R, et al.Role of oxygen-enriched atomization in kerosene spray flames[J].Journal of Propulsion and Power, 2000, 16(5):845-852.
[17]	Gupta A K, Damm T, Cook C, et al.Effect of oxygen-enriched atomization air on the characteristics of spray flames.Reno:35th Aerospace Sciences Meeting, 1997.
[18]	Bane S P M, Ziegler J L, Boettcher P A, et al.Experimental investigation of spark ignition energy in kerosene, hexane, and hydrogen[J].Journal of Loss Prevention in the Process Industries, 2013, 26(2):290-294.