Abstract
A thermal barrier coating forms a high temperature resistant metal by the spraying of ceramics or other materials. Thermal barrier coatings are mainly used in the aviation field because they can significantly improve the thermal resistance of the aircraft engine turbine blades, combustion chamber and the other hot parts. In this paper, a thermal barrier coating model of the combustion chamber is established by using the finite element method. The stress field and displacement field of thermal barrier coatings under different thicknesses of the thermally grown oxide layer and thermal barrier coating layer, and the maximum operating temperature were studied. The results show that stress and deformation under the three thermal cycles increase with the increase in operating temperature and the thickness of thermally grown oxide (TGO) and thermal barrier coat (TBC), except for the case of TGO thickness of 2 μm.
Highlights
IntroductionThermal barrier coating systems are widely used in the combustion chamber, the turbine blade and etc., due to their advantages of improving the durability of the hot parts
Thermal barrier coating systems are widely used in the combustion chamber, the turbine blade and etc., due to their advantages of improving the durability of the hot parts.The thermal barrier coating system is composed of the bond coat (BC), the thermally grown oxide (TGO), the thermal barrier coat (TBC) and the substrate as shown in Figure 1 [1,2,3]
The thermal barrier coating systems can decrease the temperature from the ceramic layer to the underlying superalloy substrate due to the thermally grown oxide which is formed via oxidation
Summary
Thermal barrier coating systems are widely used in the combustion chamber, the turbine blade and etc., due to their advantages of improving the durability of the hot parts. The thermal barrier coating system is composed of the bond coat (BC), the thermally grown oxide (TGO), the thermal barrier coat (TBC) and the substrate as shown in Figure 1 [1,2,3]. The thermal barrier coating systems can decrease the temperature from the ceramic layer to the underlying superalloy substrate due to the thermally grown oxide which is formed via oxidation. The nickel alloy was widely used to form an underlying superalloy substrate, and the BC is composed of MCrAlY alloy. A substantial level of stress is generated within the TGO layer, as the TBC system is subjected to thermal cycling. The induced stress can cause the TGO layer to separate, buckle and even crack [4,5]
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