| 跨声速涡轮静子端壁气膜冷却数值研究 |
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| 引用本文： | 李宁坤,闻洁.跨声速涡轮静子端壁气膜冷却数值研究[J].航空发动机,2011,37(3):50-54. |
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| 作者姓名： | 李宁坤 闻洁 |
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| 作者单位： | 北京航空航天大学能源与动力工程学院,北京,100191 |
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| 摘 要： | 对跨声速涡轮静子端壁气膜冷却进行了数值研究。研究发现涡轮静子端壁存在几个强换热区域：叶片前缘马蹄涡及前缘马蹄涡区域、吸力面马蹄涡分支覆盖区域、通道中靠近压力面侧和尾缘附近及尾缘后区域。针对端壁区域复杂的换热分布,设计了1种新型端壁全气膜冷却布置。通过数值研究对比了在不同进口吹风比情况下的壁面Nu、壁面气膜冷却效果和壁面热负荷。结果表明：存在最佳的进口吹风比,即在前缘Minlet=1.0时,尾缘Minlet=4.0时,端壁区域冷却效果最好。
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| 关 键 词： | 涡轮静子端壁 换热 全气膜冷却 进口吹风比 |
Numerical Study on Flim Cooling of Transonic Turbine Vane Endwall |
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| Authors: | LI Ning-kun WEN Jie |
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| Institution: | LI Ning-kun,WEN Jie(School of Jet Propulsion,Beihang University,Beijing 100191,China) |
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| Abstract: | The numerical study was conducted on the endwall film-cooling of transonic turbine vane.Several regions of high heat transfer rate were presented on turbine vane endwall.They are leading edge region where the horseshoe vortex occurs,suction side region where horseshoe vortex happens,channel region near the pressure side,and region near the trailing edge and downstream of trailing edge.According to the complex heat transfer distribution on the endwall,a new full film cooling holes on the endwall was designed... |
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| Keywords: | turbine vane endwall heat transfer film cooling inlet blowing ratio |
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