涡轮间燃烧室贫油熄火特性的试验研究  

Experimental Study on Lean Blow-Out Characteristic of Inter-stage Turbine Burner

作　　者：宋双文[1] 胡好生[1] 王梅娟[1] 陈剑[1] 

机构地区：[1]中航工业航空动力机械研究所,湖南株洲412002

出　　处：《航空发动机》2012年第5期10-12,35,共4页Aeroengine

摘　　要：以应用于某涡轴发动机的涡轮级间燃烧室为研究背景,设计并加工多方案3头部涡轮级间燃烧室试验件,试验研究了主流马赫数、主流温度、凹腔深宽比和凹腔后体高度变化对其贫油熄火性能的影响。试验结果表明:贫油熄火余气系数随主流马赫数的增大而减小,随主流温度的升高而增大,但主流温度的变化不如主流马赫数变化对贫油熄火性能的影响大;后体进气量的增加对提高贫油熄火性能有利;凹腔深宽比和凹腔后体高度的变化对贫油熄火性能有一定影响;深宽比为0.8、后体高度为30 mm且在后体开槽的试验件的贫油熄火性能最好。Muhimode three dome Inter-stage Turbine Burner（ITB） test pieces were designed and manufactured based on a turboshaft engine. The effect of the Mach number of main air, the temperature of main air, the ratio of the depth and width of cavity and the height of after body of cavity on Lean Blow-Out （LBO） characteristics was studied by the experiment. The results show that LBO excess air coefficient decreases with the Mach number of main air increase and increases with the main air temperature increase, but the changing of temperature has less impact on LBO characteristics compared with the Mach number. Increasing the airflow from the after body of cavity helps to improve LBO performance. The ratio of the depth and width and the height of after body has definite effect on LBO performance. LBO characteristics is the best when the ratio of the depth and width is 0.8, the height of after body is 30 mm and the after body of cavity is slotting.

关 键 词：涡轮间燃烧室 驻涡燃烧室 凹腔 贫油熄火 试验研究 涡轴发动机 

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]