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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.
A new composite cooling structure of micro-channel gas film used in turbine guide vane is studied by means of numerical simulation. The emphasis is on the structural design and structural optimization of the novel composite cooling method for micro-channels and gas film holes, The results show that different composite cooling structures have different effects on cooling efficiency and pressure loss. Among the several composite structures designed, the branching and small channel structure has the same effect on the balance of cooling efficiency and pressure The calculated results of several composite structures show that the cooling efficiency of the novel composite cooling structure of the micro-channel airfoil is higher than the cooling efficiency of the casting cold blade, and the cooling effect is good, which has great application prospect.