涡轮叶片微小通道气膜新型复合冷却结构设计

孙纪宁; 邓晶; 邓宏武

涡轮叶片微小通道气膜新型复合冷却结构设计

北京航空航天大学航空发动机气动热力重点实验室, 北京 100191

详细信息

中图分类号: V 231.1
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出版历程
- 收稿日期: 2011-11-28
- 网络出版日期: 2012-05-30

Structure design of a new cooling system combined micro channel and film cooling in the turbine blade

National Key Laboratory on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 利用数值模拟的方法,研究了一种应用于涡轮导向器叶片的微小通道气膜新型复合冷却结构.重点是对微小通道和气膜孔的新型复合冷却方法进行结构设计并进行结构优化,探讨不同的冷却结构形式对流动和换热的影响.研究表明:不同的复合冷却结构对冷却效率和压力损失的影响不同;在所设计的几种复合结构中,分枝小通道结构在平衡冷却效率和压力损失方面有着较好的效果;所计算的几种复合结构的结果都显示,微小通道气膜新型复合冷却结构的冷却效率高于铸冷叶片的冷却效率,冷却效果好,具有巨大的应用前景.
- 微小通道 /
- 气膜冷却 /
- 冷却效率 /
- 压力损失
Abstract: Numerical simulation was used to investigate a new compound cooling system, which combines micro channel and film cooling together in a guide turbine vane. Research was focused on the optimization design of these new organizational structures, in order to discuss the different effect on the characteristics of flow resistance and heat transfer. In these designed structures, branching channel structure in balancing cooling efficiency and the pressure loss has good effects. The computational results also show that the cooling efficiency of this compound cooling structure is higher than the cast-cooling blade. The prospect of the compound structure applied to turbine cooling system is huge.
- micro channel /
- film cooling /
- cooling efficiency /
- pressure loss

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参考文献(9)

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