PVD thermal barrier coating applications and process development for aircraft engines

被引：71

作者：

Rigney, DV ^{[1
]}

Viguie, R ^{[1
]}

Wortman, DJ ^{[1
]}

Skelly, DW ^{[1
]}

机构：

[1] GE AIRCRAFT ENGINES,CINCINNATI,OH 45215

来源：

JOURNAL OF THERMAL SPRAY TECHNOLOGY | 1997年 / 6卷 / 02期

关键词：

electron beam physical vapor deposition; high-pressure turbine airfoils; process parameters; thermal barrier coatings; yttria-stabilized zirconia;

D O I：

10.1007/s11666-997-0008-6

中图分类号：

TB3 [工程材料学];

学科分类号：

0805 ; 080502 ;

摘要：

Thermal barrier coatings (TBCs) have been developed for application to aircraft engine components to improve service life in an increasingly hostile thermal environment. The choice of TBC type is related to the component, intended use, and economics. Selection of electron beam physical vapor deposition processing for turbine blade is due in part to part size, surface finish requirements, thickness control needs, and hole closure issues, Process development of PVD TBCs has been carried out at several different sites, including GE Aircraft Engines (GEAE). The influence of processing variables on microstructure is discussed, along with the GEAE development coater and initial experiences of pilot line operation.

引用

页码：167 / 175

页数：9