轴向分级环形燃烧室点火机理的实验研究  

Experimental study of ignition mechanism in an axially staged annular combustor

作　　者：曾琦 朱志新 于皓 曹俊 黎超超 王良 郑耀[1] 夏一帆[1] 王高峰[1] ZENG Qi;ZHU Zhixin;YU Hao;CAO Jun;LI Chaochao;WANG Liang;ZHENG Yao;XIA Yifan;WANG Gaofeng(School of Aeronautics and Astronautics,Zhejiang University,Hangzhou 310027,China;AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China)

机构地区：[1]浙江大学航空航天学院,浙江杭州310027 [2]中国航发湖南动力机械研究所,湖南株洲412002

出　　处：《推进技术》2025年第2期145-153,共9页Journal of Propulsion Technology

基　　金：国家自然科学基金(51976184);国家科技重大专项(J2019-Ⅲ-0006-0049)。

摘　　要：本文针对涡轴发动机燃油轴向分级低排放燃烧组织方案,开展了周向点火机理研究。设计搭建了一种预燃级后置斜喷的环形可视化模型燃烧室实验平台,采用高速光学诊断方法,对不同流量、当量比和主/预燃级匹配位置对周向点火联焰过程进行了实验测量,分析了周向点火联焰过程的火焰传播模式,获得了环形燃烧室点火和贫油熄火边界。实验结果表明,当预燃级喷嘴中心轴线正对主燃级头部中心时,燃油周向顺时针和逆时针斜喷的周向联焰过程都为单向逆时针传播模式;当两者中心线错开时,周向联焰过程呈双向传播模式。在预燃级喷嘴斜喷方向与主燃级头部旋流方向一致的情况下,逆时针方向的火焰锋面沿燃烧室外壁传播,而顺时针方向的火焰峰面沿内壁传播。将预燃级喷嘴设置于主燃级相邻两头部中间时,周向联焰时间与贫油点熄火边界综合性能最佳,其周向联焰时间短至156 ms,点火极限当量比为0.16,贫油熄火边界当量比低至0.065。This paper investigated the light-round mechanism in the axially-staged low-emissions combus⁃tion organization scheme of turboshaft engines.An annular transparent model combustor platform is designed and constructed with down-stream installing of the pilot stage’s oblique injector.The light-round processes under dif⁃ferent flowrates,equivalence ratios and the matching positions of the main/pilot stages are experimentally stud⁃ied,using high-speed optical diagnostics.The flame propagation patterns of the light-round process were anal⁃ysed;the ignition limits and lean blow off boundaries of the annular combustor were obtained.Experimental re⁃sults show that when the centre axis of the pilot stage’s injector is aligned with the centre of the main stage’s burner,the light-round process under anti-clockwise and clockwise fuel injection shows a single anti-clockwise propagation mode.When their centre axes are offset,the light-round process exhibits a bi-directional propaga⁃tion mode.When the inclined direction of the pilot stage’s injector is consistent with the swirling direction of the main stage’s burner,the anti-clockwise flame front propagates along the combustor’s outer wall;and the clock⁃wise one propagates along the inner wall.Setting the pilot stage’s injector between two adjacent main stage’s burners results in the optimal comprehensive performance of the light-round time,ignition limit and lean blow off boundary.Its light-round time is shortened to156 ms;the equivalence ratio of the ignition limit is 0.16;and the equivalence ratio of lean blow off is reduced to 0.065.

关 键 词：环形燃烧室 轴向分级 光学诊断 周向点火联焰 点熄火边界 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]