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采用实验的方法,研究带交错肋结构和纵向隔板的涡轮叶片内冷通道的流动与换热.实验采用相变加热的方法,为模型实验件提供等壁温边界条件,实验在Re=10 000~60 000之间进行.实验模型采用了交错肋结构和扰流柱结构,分别与两种纵向隔板组合进行实验,以期望得到综合传热效果最优的组合.实验件的一侧外壁面被分成10个区域以期望了解实验件局部换热情况.实验结果表明:带交错肋结构的通道的换热效果好于带扰流柱结构的通道的换热效果.当Re<30 000时,综合传热性能最佳的是带波形隔板加交错肋0612组合结构的通道,当Re>30 000时,综合传热性能最佳的是带波形隔板加交错肋0412组合结构的通道.
The experimental method was used to study the flow and heat transfer in the cooling channels inside the turbine blades with staggered rib structure and longitudinal baffle.The phase boundary heating conditions were provided for the model experiment by experiment of phase change heating.The experiments were carried out with Re = 10 000 ~ 60 000. The experimental model adopts the staggered rib structure and the spoiler structure, respectively, with two longitudinal baffle combination experiments, in order to expect the best combination of heat transfer effect of the experimental side of the outside The wall surface is divided into 10 zones in order to know the local heat transfer of experimental parts.The experimental results show that the heat transfer effect of the channel with staggered rib structure is better than that of the channel with the spoiler structure.When Re <30 000 , The best overall heat transfer performance is the channel with corrugated separator plus staggered rib 0612 composite structure. When Re> 30 000, the best overall heat transfer performance is the corrugated separator plus staggered rib 0412 combined structure.