孔阵排列和偏转角对多斜孔壁火焰筒冷却效果的影响研究  

Numerical Study on Cooling Effects of Hole Arrangement and Deflected Angle of Inclined Multi-hole on Annular Flame Tube

作　　者：刘常春[1] 吉洪湖[1] 杨芳芳 张勃[1] 郑妹[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]上海空间推进研究所发动机研究室,上海201112

出　　处：《推进技术》2013年第10期1369-1375,共7页Journal of Propulsion Technology

摘　　要：为了研究火焰筒上孔阵排列和偏转角对多斜孔壁冷却效果的影响规律,将多斜孔壁冷却结构应用到航空发动机的燃烧室火焰筒壁上,通过数值模拟研究了不同孔阵排列和不同偏转角的共6种多斜孔结构对火焰筒壁的冷却效果,包括有效温比和对流换热系数的比较。结果表明:在燃烧室上,孔阵排列对多斜孔壁冷却效果的影响与平板模型的规律一致,叉排孔阵排列优于顺排孔阵排列,孔排周向位移找到了冷却效果较好时的孔排周向位移值;在火焰筒前端,偏转角的选取应考虑到旋流器对流场的影响,而在火焰筒后端,偏转角为0°的冷却效果较好。Numerical simulation was performed on the annular flame tube in aero-engine combustor with inclined multi-hole applied. Six different structures of inclined multi-hole were studied in order to analyze the cooling effects of hole arrangement and deflection angle on the wall of annular flame tube by comparison of cooling effectiveness and heat transfer coefficient. Results show that, in aero-engine combustor, the cool- ing effect of the hole arrangement is about the same as in the flat. Staggered arrangement is better than a- ligned arrangement. The circumferential displacement is obtained for the better cooling effects. In the front tube, the deflected angle should be selected according to the effects of the swirler. At the back of the tube, when the deflected angle is 0°, the cooling effect is among the best.

关 键 词：航空发动机 燃烧室 火焰筒 多斜孔壁冷却 孔阵排列 偏转角 数值模拟 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]