冲击+同向对流+气膜冷却效果的试验
Experimental study of cooling effectiveness of impingement/cocurrent convection/film cooling
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摘要: 为了研究火焰筒壁面冲击+同向对流+气膜复合冷却方式的冷却效果,设计了多种不同几何结构的试验件,采用红外热像仪对冷却壁温进行测量.研究结果表明,冷却效率随吹风比的增加而增大.沿冷却壁面,冷却效率呈波浪型分布.在气膜出口附近区域和冲击驻点区域冷却效率最高.在冲击驻点区域后,冷却效率的下降较为缓慢.冷却效率随冲击间距的减小而增大.Abstract: In order to study the heat transfer characteristics of impingement/cocurrent convection/film double cooling,several test pieces were designed.The experimental results show that the cooling efficiency increases with the growing blowing ratio;the distribution of cooling efficiency is wavy on the cooling wall.The cooling efficiency is higher in the areas of cooling film exit and the impingement stagnant point.The decrease of cooling efficiency is weakened behind the impingement stagnant point.Cooling efficiency increases with the decrease of impingement space.
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Key words:
- aero-engine /
- flame tube /
- impinging cooling /
- film cooling /
- convective heat transfer
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