涡轮叶片尾缘复合通道的换热

Heat transfer in complex passages of turbine blade trailing edge

采用热色液晶测温法 ,测量了涡轮叶片尾缘带隔板的复合通道的温度场 ,分析了射流冲击强化扰流柱通道内换热的机理 ,讨论了两通道间隔板的不同开孔结构对换热的影响 .从工程应用的角度出发提出了几个换热评价指标 ,对不同开孔结构的隔板进行了换热评价 .结果表明 :冷气由第 1通道进入 ,通过隔板上的孔不断由径向流动变为弦向流动后 ,对第 2通道的扰流柱区形成冲击 ,最后由劈缝排出 ,提高了尾缘的换热 ;开孔均匀的隔板换热效果相对较好 .

An experimental comparison research of endwall heat transfer characteristics was conducted in the complex passages of turbine blade trailing edge by using thermochromic liquid crystal method. Three kinds of diaphragm plates between two passages were studied to obtain optimal heat transfer effect. Results indicate that the radial inflow cooling air in first passage passes through the orifices in the diaphragm plates ceaselessly and changes to spanwise cooling air, which impinges the second passage and flows away through the orifices along the trailing edge, enhancing the heat transfer of trailing edge; uniform configuration of orifices in diaphragm plate provides better heat transfer effect than that of others.