| 离散孔结构超声速气膜冷却数值模拟 |
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| 引用本文： | 孙冰,王太平,张佳.离散孔结构超声速气膜冷却数值模拟[J].航空动力学报,2017,32(12):2927-2933. |
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| 作者姓名： | 孙冰 王太平 张佳 |
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| 作者单位： | 1.北京航空航天大学 宇航学院，北京 100191 |
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| 摘 要： | 为了得到气膜入口结构对气膜冷却效率的影响规律，并为工程应用提供参考，针对不同形状气膜入口结构的离散孔超声速气膜冷却展开了三维数值模拟。结果表明:气膜入口结构对气膜冷却效率影响明显，轴对称孔入口收敛段结构的流量系数直接影响冷却效果，计算工况下流量系数降低013下游冷却效率约降低005，应该防止收敛段剧烈收缩；同时，离散孔扩张段面积变化速率越小越有利于冷却，变化过快会使得冷却剂得不到充分发展，垂直主流方向的速度分量大，使得气膜往两侧流动而中心区域冷却效果变差；在非轴对称离散孔出口增加平直段能使射流更集中，可以有效防止气膜在上游被穿透造成冷却恶化现象。
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| 关 键 词： | 超声速气膜冷却 离散孔 射流孔结构 冷却效率 不均匀性 |
| 收稿时间： | 2016/5/12 0:00:00 |
Numerical simulation of discrete holes supersonic gaseous film cooling |
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| Abstract: | In order to get the effect law on the efficiency of gas film entrance structure and provide a reference for engineering application, 3D discrete holes supersonic gaseous film cooling numerical simulations with different holes structure were investigated. Results showed that the film inlet structure affected the film cooling efficiency obviously. Flow coefficient affected the cooling directly so that film cooling effectiveness reduced 005 while flow coefficient decreased 013 for the axisymmetric entrance under calculation conditions. Meanwhile, lowing jet holes area change rate enhanced the cooling effectiveness, because the flow field with too fast area change rate can't develop fully, and the gaseous film flowed to both sides while the center was exposed to combustion gas. Design of a rectifying section in discrete holes exit will help to concentrate the coolant and keep off the cooling deterioration with the layer of film penetrated. |
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| Keywords: | supersonic gaseous film cooling discrete holes jet hole structure film cooling effectiveness nonuniformity |
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