驻涡燃烧室凹腔流场结构实验  

Experiment on flow field of cavity in trapped vortex combustor

作　　者：刘玉英[1] 李瑞明[1] 杨茂林[1] 樊未军[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《推进技术》2010年第1期29-33,共5页Journal of Propulsion Technology

基　　金：航空科学基金资助项目(2006ZB51021)

摘　　要：驻涡燃烧室采用凹腔结构稳定火焰,研究凹腔内不同燃料与空气喷射情况下的流场结构非常重要。采用粒子成像测速仪(PIV)测量了驻涡燃烧室凹腔在不同主流速度下的流场,并对比分析了凹腔进气结构分别为不开冷却缝及油气渗混孔、开冷却缝不开油气渗混孔、开冷却缝和后体油气渗混孔、开冷却缝和前体油气渗混孔时的流场结构。研究结果表明,不同主流速度下所设计的不同凹腔进气结构均能在腔内形成稳定的涡,冷却缝对流场的影响较小,凹腔油气掺混孔在开孔截面上对流场及涡核中心位置的影响较大。The flow field in the cavity of trapped vortex cornbustor （TVC） is important because the cavity can provide good flame stability via trapping vortex. Under various main flow rate conditions, particle image velocimetry （PIV） was used to experimentally study the flow field inside the cavity with four kinds of fuel and air supply structures, which were natural cavity without fuel injection orifices and cooling air slots, cavity with cooling air slots but no fuel injection orifices, cavity with cooling air slots and front or back wall fuel injection orifices. It shows that stable vortex is trapped in the cavity with various fuel and air supply structures under different main flow velocity in this experiment. Cooling air slots has little effects on the cavity flow field, but fuel injection orifices have a greater impact on the flow field and the center of vortex core in the injection section.

关 键 词：驻涡燃烧室 凹腔 流动分布 粒子成像测速仪 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程]