滑动弧等离子体点火助燃头部激励对燃烧室点熄火特性的影响  

Effect of gliding arc plasma ignition and assisted combustion dome actuation on ignition and blowout characteristics of combustor chamber

作　　者：屈美娇 王宇 陈一 吴云[2] 胡长淮 许书英 QU Meijiao;WANG Yu;CHEN Yi;WU Yun;HU Changhuai;XU Shuying(Mechanical and Electrical Engineering College,Xi’an Polytechnic University,Xi’an 710600,China;National Key Lab of Aerospace Power System and Plasma Technology,Air Force Engineering University,Xi’an 710038,China;School of Mechanical Engineering,Xi’an Jiaotong University,Xi’an 710049,China;School of Aerospace Engineering,Xi’an Jiaotong University,Xi’an 710049,China)

机构地区：[1]西安工程大学机电工程学院,西安710600 [2]空军工程大学航空动力系统与等离子体技术全国重点实验室,西安710038 [3]西安交通大学机械工程学院,西安710049 [4]西安交通大学航天航空学院,西安710049

出　　处：《航空动力学报》2023年第9期2062-2072,共11页Journal of Aerospace Power

基　　金：航空发动机及燃气轮机重大专项基础研究(2017-Ⅲ-0007-0033)。

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%。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.

关 键 词：航空发动机燃烧室 滑动弧等离子体 点火助燃 着火过程 点熄火边界 

分 类 号：V233.3[航空宇航科学与技术—航空宇航推进理论与工程]