| 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。 |
| 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 |
| DOI： |
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| Numerical Study on Cooling Effects of Hole Arrangement and Deflected Angle of Inclined Multi-hole on Annular Flame Tube |
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LIU Chang-chun1, JI Hong-hu1, YANG Fang-fang2, ZHANG Bo1, ZHENG Mei1
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(1. College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;2.Aerospace Engine Research Department, Shanghai Institute of Space Propulsion, Shanghai 201112, China)
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| Abstract: |
| 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 cooling effect of the hole arrangement is about the same as in the flat. Staggered arrangement is better than aligned 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. |
| Key words: Aero-engine Combustor Flame tube Inclined multi-hole Hole arrangement Deflected angle Numerical simulation |
