旋转滑动弧涡流器点火探索试验  

Exploratory test on ignition with rotating gliding arc swirlers

作　　者：彭畅新 杨浩 刘逸博 姜世界 李元星 李炜 PENG Changxin;YANG Hao;LIU Yibo;JIANG Shijie;LI Yuanxing;LI Wei(Hunan Aviation Powerplant Research Institute,Aero Engine Corporation of China,Zhuzhou Hunan 412002,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002

出　　处：《航空动力学报》2023年第4期769-776,共8页Journal of Aerospace Power

基　　金：国防科技创新特区项目。

摘　　要：基于中小发燃烧室常用的斜切孔+径向叶片式涡流器,结合滑动弧的产生位置,开展了4种方案的旋转滑动弧涡流器设计及加工,并完成了冷态放电试验及点火试验验证。放电试验结果表明:4种方案的涡流器均能在预设位置产生稳定的旋转滑动弧。三头部点火试验结果表明:方案4的点火效果最好,其最小点火油气比低于常规点火方法。方案2次之,方案3仅能在较低的参考速度下实现燃烧室的点火,方案1的点火效果最差。滑动弧当地的气流速度及油气分布对点火效果影响显著,建议滑动弧处的气流速度不超过20 m/s。According to the position of gliding arcs,four kinds of rotating gliding arc swirlers were designed and manufactured based on the beveled holes and radial vanes swirlers commonly used in medium and small aero-engine combustors.The discharge test at cold state and ignition test were performed.The results of discharge test showed that the four swirlers could produce stable rotating gliding arcs at specific position.Ignition tests were performed based on a triple combustor.The ignition tests showed that,scheme 4 had the best ignition performance and the smallest ignition fuel-air ratio was lower if compared with conventional ignition method.The ignition performance of scheme 2 was worse than that of scheme 4.The combustor could only be ignited when the reference speed was low for scheme 3,and scheme 1 showed the worst ignition performance.The air speed and distribution of fuel air at local position of gliding arcs had a significant influence on the ignition performance and the recommended air speed was not more than 20 m/s.

关 键 词：燃烧室 旋转滑动弧 涡流器 点火 油气比 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]