热障涂层对涡轮动叶冷却效果影响的数值研究  

A numerical investigation of the influence of thermal barrier coatings on turbine rotor blade

作　　者：刘言明 侯隆安 霍玉鑫 吴思宇 贾志明 LIU Yanming;HOU Long’an;HUO Yuxin;WU Siyu;JIA Zhiming(No.703 Research Institute,China State Shipbuilding Co.,Ltd.,Harbin 150078,China;Gas Turbine R&D and Test Laboratory for Marine and Offshore Engineering,National Engineering Research Center of Special Equipment and Power System for Ship and Marine Engineering,Harbin 150078,China)

机构地区：[1]中国船舶集团有限公司第七〇三研究所,黑龙江哈尔滨150078 [2]船舶与海洋工程特种装备和动力系统国家工程研究中心,船舶及海洋工程燃气轮机研发与检测实验室,黑龙江哈尔滨150078

出　　处：《应用科技》2023年第2期17-21,共5页Applied Science and Technology

基　　金：国家科技重大专项项目(2017-Ⅱ-0006-0019).

摘　　要：为了获得涡轮叶片热障涂层隔热效果和温度分度分布规律,以带有内部冷却结构的某型燃机高压涡轮动叶为基础模型,通过气热耦合的方法对有/无热障涂层保护下的高压涡轮动叶的冷却效果进行了数值计算,并通过改变热障涂层的厚度研究了热障涂层对叶片换热的影响规律。研究发现:涂有热障涂层后,叶片温度下降明显,越靠近前缘温度降低幅度越大,压力侧与吸力侧相比温度降幅更大;厚度为0.05~0.2 mm的热障涂层可使叶片金属表面平均温度降低21~49℃;随着涂层厚度等增加,叶片金属内部的温度分布将更加均匀。In order to obtain the thermal insulation effect of thermal barrier coating on turbine blades and temperature distribution law,the aerodynamic and thermal coupling numerical calculation of the cooling effect of the rotor blades with and without thermal barrier coatings was carried out based on the rotor blades of high-pressure turbines with composite cooling structures.The influence of thermal barrier coatings on heat transfer of the blades was studied by changing the thickness of the thermal barrier coatings.The results show that the temperature of the blades with thermal barrier coating decreases obviously,and the closer to the leading edge of the blade,the greater the range of temperature decrease.The temperature drop of the pressure surface is greater than that of the suction surface.The average temperature of the blade metal surface can be reduced by 21~49℃with the coating thickness of 0.05~0.2 mm.With the increase of the thickness of thermal barrier coating,the surface temperature of the blade metal becomes more uniform.

关 键 词：燃气轮机 高压涡轮 涡轮动叶 热障涂层 涂层厚度 冷却效果 气热耦合 数值模拟 

分 类 号：TK14[动力工程及工程热物理—热能工程]