航空发动机制件热锻模激光熔覆修复层组织性能研究  

Study on Microstructure and Properties of Repaired Laser Cladding on High-temperature Forging Mould for Aeroengine Pieces

作　　者：卫广智[1] 温书涛[1] 李宝增[1] 刘其斌[1] 齐福利[1] 

机构地区：[1]贵州大学材料科学与冶金工程学院,贵州贵阳550003

出　　处：《热加工工艺》2008年第17期29-31,34,共4页Hot Working Technology

基　　金：贵州省科技型中小企业创新基金资助项目(黔科合计字[2006]5027号);贵州大学研究生创新基金资助项目(校研理工2006022);贵州大学大学生SRT项目(贵大SRT字[2007]192号)

摘　　要：为了实现对航空发动机制件热锻模具的修复,采用自配的合金粉末,利用激光熔覆技术,对报废锻压模具进行了三层熔覆修复。利用OM、XRD、显微硬度和摩擦磨损试验装置对熔覆层组织、硬度及耐磨性能进行了研究。结果表明:第一层与基材之间,第一、二层之间,第二、三层之间的结合界面均实现了良好的冶金结合;熔覆层基体相为α-Fe,基体相上分布有结晶析出的Fe5C2、Fe2B、FeSi等相;硬度在三个结合区处出现峰值,依照上面次序分别为820HV0.2、800HV0.2、760HV0.2;熔覆层具有良好的耐磨性能。To repair the high-temperature forging mould for aeroengine pieces, the failing mould were repaired three layers by laser cladding technology with self- made alloying powder. The microstructure and properties were investigated with OM, XRD, microhardness and fiction wear testing machine. The results indicate that excellent metallurgical bonding is obtained between the first cladding and the substrate, the second layer and the first layer, the third layer and the second layer. The matrix phase in cladding coating is α-Fe, some phases such as Fe2B,Fe3C and FeSi are distributed in the matrix phase. Otherwise there is an amount of amorphous. The hardness reaches three peaks（820 HV0.2,800 HV0.2,760 HV0.2 in turn respectively） in these interfaces. The coating has good wear resistance.

关 键 词：激光熔覆 修复 组织 性能 

分 类 号：TG174.44[金属学及工艺—金属表面处理] TG156.99[金属学及工艺—金属学]