Effect of gliding arc plasma ignition and assisted combustion dome actuation on ignition and blowout characteristics of combustor chamber
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摘要:
基于旋转滑动弧等离子体技术，研制了与某型航空发动机适配的点火助燃头部，并在三头部燃烧室实验平台的基础上开展了点熄火特性实验研究，通过分析旋转滑动弧等离子体点火助燃头部激励对燃烧室着火过程、点火边界以及熄火边界的影响规律，初步验证了该技术拓展燃烧室点熄火性能的可行性。结果表明：旋转滑动弧等离子体激励可以显著拓宽点熄火边界，缩短着火延迟时间。相比于常规点火器，在余气系数为2，输入电压为200 V时，着火延迟时间缩短49.2%；输入电压为200 V时，贫油点火边界拓宽18.2%；输入电压为240 V时，熄火边界拓宽7.41%。
Abstract:The ignition and assisted combustion dome was developed based on rotating gliding arc discharge plasma, and it was preliminarily validated that the ignition and assisted combustion dome can widen the ignition and flameout performance of combustor. Experiments were carried out on the combustion experiment platform with three combustion domes to analyze the effect law of rotating gliding arc plasma actuation on the combustion of aero-engine, including igniting fire process, lean ignition limit and lean blowout limit. Results showed that rotating gliding arc plasma actuation can significantly broaden ignition and lean blowout limit and shorten the delay time of ignition. Compared with conventional electric spark igniter, the delay time was reduced by 49.2% when the input voltage was 200 V and excess air coefficient was 2. The ignition limit under lean oil condition was widened by 18.2% when the input voltage was 200 V, and lean flameout limit was widened by 7.41% when the input voltage was 240 V.
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图 1 航空发动机燃烧室实验平台结构示意图
Figure 1. Schematic of aero-engine combustion chamber experimental platform
图 2 航空发动机三头部燃烧室实验装置照片
Figure 2. Photograph of aero-engine three dome combustion chamber experimental apparatus
图 5 点火助燃头部放电时活性粒子的流动轨迹设想图
Figure 5. Flow trajectory diagram of active particles under ignition and assisted combustion dome within electric discharge
图 6 三头部燃烧室点火助燃头部放电照片
Figure 6. Photograph of ignition and assisted combustion dome three dome combustion chamber within electric discharge
图 8 常规点火器点火的着火过程（α=0.4）
Figure 8. Igniting fire process of conventional electric spark ignition （α=0.4）
图 9 滑动弧等离子体点火的着火过程（α=0.4，U0=200 V）
Figure 9. Igniting fire process of gliding arc plasma ignition （α=0.4, U0=200 V）
图 10 常规点火与滑动弧等离子体点火的OH发射强度随时间的变化曲线（α=0.4）
Figure 10. The curve of OH emission intensity of conventional ignition and gliding arc plasma ignition （α=0.4）
图 12 常规点火器与等离子体点火助燃头部的点火特性
Figure 12. Ignition characteristics of conventional igniter and plasma ignition and assisted combustion dome
图 13 临近熄火状态下OH强度分布（U0=240 V）
Figure 13. Intensity distribution of OH approaching flameout （U0=240 V）
图 14 常规燃烧与等离子体助燃的贫油熄火边界
Figure 14. Lean flameout limit of conventional combustion and plasma-assisted combustion
表 1 实验条件表
Table 1. Table of experimental conditions
研究内容 进口速度
C3/（m/s）余气系数
α输入电压
U0/V点火延迟 30 0.4～2.0 0（常规）
160～240点火边界 40～80 熄火边界 50～130 
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