驻涡燃烧室掺混孔对流量分配及燃烧性能的影响  

Impact of dilution holes on the flow rate distribution and combustion performance of trapped vortex combustor

作　　者：李瑞明[1] 刘玉英[1] 马文杰[1] 张荣春[1] 柳杨[1] 杨茂林[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：《航空动力学报》2010年第3期488-495,共8页Journal of Aerospace Power

基　　金：航空科学基金(2006ZB51021)

摘　　要：数值模拟了三种不同掺混孔面积对二元模型驻涡燃烧室试验器流量分配的影响,并在进口马赫数约为0.3、进口温度约为540 K工况条件下,分别对其进行了试验研究,对比分析了它们的总压损失、贫熄边界和燃烧效率.研究表明:掺混孔面积对流量分配影响较大,在本试验条件下,掺混孔面积较大的驻涡燃烧室试验器的燃烧性能优于其余两种.The impact of dilution holes with three different areas on the flow rate distribution of a model rectangular trapped vortex combustor was numerically simulated, and the total pressure loss, lean blow off limit and combustion efficiency of the combustor were ex- perimentally studied under the inlet Mach number was 0.3 and the total temperature was 540 K. This shows that, both the flow rate distribution and the performance of the combustor are affected by the dilution holes＇areas, and the combustor with larger dilution holes has better combustion performances than the others.

关 键 词：驻涡燃烧室 掺混孔 流量分配 燃烧性能 

分 类 号：V235.11[航空宇航科学与技术—航空宇航推进理论与工程]