scholarly journals Development of Coating Design System for Gas Turbine, IV. Basic Study of Oxidation Behavior of Zirconia Thermal Barrier Coating at High-Temperature.

1998 ◽  
Vol 47 (7) ◽  
pp. 665-671 ◽  
Author(s):  
Yoshiyasu ITOH ◽  
Masashi TAKAHASHI ◽  
Yutaka ISHIWATA ◽  
Kohsoku NAGATA
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Thermal Barrier Coating ◽  
Oxidation Behavior ◽  
Design System ◽  
Thermal Barrier ◽  
Basic Study ◽  
Barrier Coating ◽  
Coating Design

Development of Advance Thermal Barrier Coating in Gas Turbine

2010 ◽  
Vol 123-125 ◽  
pp. 459-462
Author(s):  
Choul Jun Choi ◽  
Jung Ki Lee ◽  
Lee Ku Kwac ◽  
Jae Yeol Kim
Keyword(s):  
Heat Transfer ◽  
High Temperature ◽  
Gas Turbine ◽  
Thermal Barrier Coating ◽  
Base Metal ◽  
Surface Profile ◽  
Thermal Barrier ◽  
Metal Base ◽  
Combustion Gas ◽  
Barrier Coating

Combustion gas of gas turbine is about 1100 ~ 1300 °C. Is doing TBC(Thermal Barrier Coating) on the base metal surface to protect rotor or blade from high temperature flame. TBC system reduced heat transfer as metal base metal. TBC system is divided by bond coating of prevent oxidation and corrosion and Top coating reduced of heat transfer by high Temperature flame. The objective of this study was to development of an advance TBC system for high Temperature (>1350°C) gas turbine components. Used coating powder developed newly in coating process, and more than 1350°C by parameter control in usable coating method develop. Internal studies looked at the effect of TBC coating thickness, material chemistry, substrate composition, surface temperature and bond coat as-sprayed surface profile/particle size on technical performance.

Research on High Temperature Combustor for Advanced Reheat Gas Turbine

1986 ◽  
Author(s):  
K. Mori ◽  
J. Kitajima ◽  
T. Kimura ◽  
T. Nakamura
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Thermal Barrier Coating ◽  
Ceramic Tile ◽  
Cooling System ◽  
Thermal Barrier ◽  
Outlet Temperature ◽  
National Project ◽  
Barrier Coating ◽  
Double Wall

Preliminary studies on the high temperature combustors (combustor outlet temperature = 1670–1770K) for the prototype advanced reheat gas turbine were carried out under the national project of Japan - Moonlight Project. This paper describes an outline of the studies; (i) application of an advanced ceramic thermal barrier coating and ODS superalloy, (ii) development of the advanced double-wall cooling system, (iii) research on the ceramic tile combustor.

Durability Evaluation of Thermal Barrier Coating (TBC) at High Temperature

2013 ◽  
Vol 467 ◽  
pp. 29-34
Author(s):  
Hyun Woo Song ◽  
Yong Seok Kim ◽  
Jae Mean Koo ◽  
Chang Sung Seok
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
High Temperature ◽  
Gas Turbine ◽  
Thermal Barrier Coating ◽  
Thermal Barrier ◽  
Element Analysis ◽  
Barrier Coating ◽  
The Finite Element Analysis ◽  
Comparison Of The Results

Thermal barrier coating (TBC) which protects the gas turbine from high temperature is damaged by repeated thermal fatigue [1,2]. Generally, damage of top coating of thermal barrier coating is resulted in damage to the entire gas turbine. Thus, the durability of the thermal barrier coating should be evaluated to protect the gas turbine from damage. In general, the major cause of delamination in the top coating is the thermal stress at its interface according to the change in temperature [. In this research, parallel stress at the top coating interface (S11) was verified as the major cause of delamination by finite element analysis. In order to evaluate the durability of the TBC, we need information about the parallel strength at the interface, but it is difficult to measure. Furthermore, we verified the relationship between the stress perpendicular to the interface (S22) and the stress parallel to the interface (S11) by finite element analysis. The durability of the thermal barrier coating was evaluated by comparison of the results of the bond strength test of Kim et al. with the results of the finite element analysis of this research.

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