| 학회 |
한국재료학회 |
| 학술대회 |
2010년 봄 (05/13 ~ 05/14, 삼척 팰리스 호텔) |
| 권호 |
16권 1호 |
| 발표분야 |
H. Advanced Coating Techniques(첨단 코팅 기술) |
| 제목 |
1300도급 가스터빈 1단 블레이드의 코팅을 이용한 열화평가 |
| 초록 |
The first stage blade of gas turbine is operated severe environments which include both above 1300 ℃ high temperature gas and thermal stress by high speed rotation of 3600 rpm and internal cooling system. To obtain more efficiency by increasing fire temperature, internal cooling channel and Thermal Barrier Coating(TBC) system have been used. A TBC system is multilayer coating system that consists of a ceramic outer layer(top coating) and a metallic inner layer(bond coat) between the ceramic and substrate. The main purpose of top coat is thermal barrier for hot gas and bond coat acts as a buffer against thermal stress by difference of thermal expansion coefficient between ceramic and substrate, a reservior that improves the resistance oxidation or resistance corrosion. The aim of this study is to evaluate properties of bond coat which was used on 1300℃ class gas turbine blade and to know degradation of coating layer. There was occurred inter-diffusion layer between bond coat and substrate due to high temperature exposure. the thickness of bond coat of suction side is thicker than pressure side. highest thickness of inter-diffusion zone is shown the S1 near leading edge. The chemical composition analysis on bond coat showed aluminum depletion around inter diffusion layer. And the operating temperature of blade is estimated by inter-diffusion zone thickness measurement. |
| 저자 |
송태훈, 장중철, 김범수
|
| 소속 |
한전전력(연) |
| 키워드 |
Thermal barrier coat; inter-diffusion zone; blade; degradation
|
| E-Mail |
|
