平面激光诱导荧光技术在超声速燃烧中的应用  

Application of PLIF in research on supersonic combustion

作　　者：李麦亮[1] 周进[1] 耿辉[1] 翟振辰[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2004年第4期381-384,共4页Journal of Propulsion Technology

基　　金：国家"八六三"基金项目;国防科技大学研究生创新基金。

摘　　要：使用283.553nm的紫外激光激发对温度不敏感的氢氧基Q1(8)线,拍摄代表氢氧基浓度分布的受激荧光发射图像,以此来分析超声速燃烧火焰的结构。用这种方法研究了不同凹腔长深比、凹腔后缘倾角和不同燃料喷注方案对超声速燃烧火焰结构的影响。观察到了凹腔与激波对点火和火焰稳定的作用,凹腔长深比和后缘倾角对燃料穿透、混合和燃烧的不同扰动作用,以及火焰中存在明显的湍流结构和分区燃烧现象,并进行了简要分析。结果显示PLIF是超声速燃烧研究的有力工具。The flame structure of supersonic combustion was obtained by means of hydrogen oxygen radical (OH) PLIF imaging. The fluorescence image of OH was induced by UV laser tuned to 283.553 nm. Then the influence on flame structure of supersonic combustion of ratio of length and deep of cavity, obliquity of back edge of cavity and different schemes of fuel injection were studied. It was observed that function of cavities and shock wave on ignition and flame holding. It was also analyzed that the influence of ratio to Length to Deep (L/D) and obliquity of back edge of cavity on fuel penetration, mixing and combustion based on OH PLIF images. The obvious turbulent structure and zonal combustions were found in these images and such phenomena were discussed briefly. Studies show that PLIF is a powerful tool for the supersonic combustion research.

关 键 词：超音速燃烧 激光技术 流动分布 火焰 

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]