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高压燃气涡轮叶片采用内部冲击和外部气膜冷却相结合的复合冷却结构来提高叶片的冷却效率。本研究应用流热耦合的方法计算涡轮叶片中弦区的复合冷却效果,在不同的冲击孔与气膜孔间距l/d1以及不同的冲击孔长度h/d1复合冷却结构中,得到不同冷气流量条件下的冷却传热特性和流动阻力特性,建立了冷却效率与结构特征参数的关联式。结果表明:在冲击孔与气膜孔间距l/d1=12的复合冷却结构中,平板外表面气膜孔上下游的冷却效率均保持较高值;在冲击孔长度l/d1=1的复合冷却结构中,气膜孔上游区域的冷却效率较高。复合冷却结构中气膜孔下游的冷却效率不受冲击孔与气膜孔间距l与冲击孔长度h的影响。
High-pressure gas turbine blades using a combination of internal impact and external film cooling composite cooling structure to improve the cooling efficiency of the blade. In this study, the cooling effect of the chord zone in the turbine blade was calculated by using the flow-heat coupling method. Different cooling air flow rates were obtained in different composite cooling structures with a distance l / d1 of the impact hole and the film hole and different impact hole length h / d1 Conditions of the cooling heat transfer characteristics and flow resistance characteristics of the establishment of the cooling efficiency and structural characteristics of the correlation parameters. The results show that the cooling efficiency both upstream and downstream of the gas film hole in the outer surface of the plate maintains a high value in the composite cooling structure with a spacing l / d1 = 12 of the impact hole and the gas film hole. When the length of the impact hole is l / d1 = 1 In the cooling structure, the cooling efficiency in the upstream region of the film hole is higher. The cooling efficiency of the downstream of the film hole in the composite cooling structure is not affected by the distance l between the impact hole and the film hole and the length of the impact hole h.