带肋通道和气膜冷却交互下的绝热和耦合传热研究  

Research on the Interaction of Ribbed Passage and Film Cooling in Adiabatic and Coupling Condition

作　　者：陈娉婷[1] 秦晏旻[1] 任静[1] 蒋洪德[1] 

机构地区：[1]清华大学热能工程系,北京100084

出　　处：《工程热物理学报》2016年第7期1422-1426,共5页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.51376099)

摘　　要：燃气轮机透平叶片冷却中,内部肋片扰流对气膜冷却效果有显著影响,当边界条件为金属壁面绝热和金属壁面耦合时,冷却效率会有不同的表现。本文采用数值计算方法,分别计算绝热边界和耦合边界条件下,气膜孔进口与内部冷却扰流肋片不同相对位置条件下的绝热气膜冷却效率和耦合条件下的整体冷却效率进行计算。结果表明当气膜进口位于肋后扰流区时,绝热气膜冷却效率较差。绝热边界和耦合边界条件下流场相似,气膜孔与肋片相对位置对于气膜孔下游整体冷却效率的影响与绝热条件相似。The turbulence of ribs in internal cooling channel has great impact on film cooling in gas turbine blade cooling.The cooling effect differs between the adiabatic boundary condition and the coupling condition.The impact on cooling effects of the relative position between the inlet of film hole and the ribs was investigated on both adiabatic and diabatic boundary conditions.When the inlet of film hole was just behind a rib,the cooling effect was bad.The flow fields were similar on both adiabatic and diabatic boundary conditions.The effects on cooling effects of the relative position between the inlet of film hole and the ribs are similar.

关 键 词：气膜冷却 耦合 内部冷却 相对位置 肋片 

分 类 号：TK474.7[动力工程及工程热物理—动力机械及工程]