High-temperature resistant component and gas turbine hot part
View Patent ↗A high-temperature resistant component for, e.g., a gas turbine hot part, includes an alloy substrate containing Ni, Co, or Fe as the principal component, and a thermal barrier coating formed over the surface of the substrate via a bond coat. The thermal barrier coating includes a porous thermal-barrier layer made of ceramic and an environmental barrier layer with corrosion resistance. An impregnated layer is provided between the environmental barrier layer and the thermal barrier layer. In the impregnated layer, the thermal barrier layer is impregnated with a part of the environmental barrier layer. The thermal barrier layer is made of a porous zirconia layer, and the environmental barrier layer includes silica as the principal component. The porous zirconia layer has pores impregnated with the part of the environmental barrier layer. As a result, the high-temperature resistant component has excellent corrosion resistance and excellent heat resistance.
1. A high-temperature resistant component comprising:
a substrate containing an alloy including Ni, Co, or Fe as a principal component;
a bond coat being formed on the substrate and including an alloy; and
a thermal barrier coating being formed on the bond coat,
wherein the thermal barrier coating comprises a thermal barrier layer formed on the bond coat and containing porous ceramic, an impregnated layer formed on the thermal barrier layer, and an environmental barrier layer formed on the impregnated layer and consisting of silica glass, the impregnated layer being a layer in which pores of the porous ceramic of the thermal barrier layer are impregnated with a part of the silica of the environmental barrier layer, and the environmental barrier layer having a thickness of 0.05-0.1 mm.
2. The high-temperature resistant component according to claim 1 , wherein the thermal barrier layer contains zirconia.
3. The high-temperature resistant component according to claim 1 , wherein the environmental barrier layer has a porosity of 5% or less.
4. The high-temperature resistant component according to claim 1 , wherein the thermal barrier layer has a thickness of 0.1-1 mm.
5. The high-temperature resistant component according to claim 1 , wherein the thermal barrier layer has a porosity of 10-30%.
6. The high-temperature resistant component according to claim 1 , wherein the environmental barrier layer is formed using a solution containing a silica precursor.
7. A gas turbine hot part using the high-temperature resistant component according to claim 1 .
8. The gas turbine hot part according to claim 7 , wherein the gas turbine hot part is a bucket.
9. The gas turbine hot part according to claim 7 , wherein the gas turbine hot part is used in a corrosive environment with use of low-grade oil.
10. The high-temperature resistant component according to claim 1 , wherein the environmental barrier layer consists of silica glass with 90% or more purity of silica.
11. The high-temperature resistant component according to claim 1 , wherein the thermal barrier layer comprises partially-stabilized zirconia.
12. The high-temperature resistant component according to claim 1 , wherein the bond coat is an alloy layer made of a MCrAlY alloy or MCrAl alloy where M is at least one element selected from the group consisting of Fe, Ni, and Co.
13. A high-temperature resistant component comprising:
a substrate containing an alloy including Ni, Co, or Fe as a principal component;
a bond coat being formed on the substrate and including an alloy; and
a thermal barrier coating being formed on the bond coat,
wherein the thermal barrier coating comprises a thermal barrier layer formed on the bond coat and containing porous ceramic, an impregnated layer formed on the thermal barrier layer, and an environmental barrier layer formed on the impregnated layer and consisting of silica glass, the impregnated layer being a layer in which pores of the porous ceramic of the thermal barrier layer are impregnated with a part of the silica of the environmental barrier layer, and the impregnated layer having a thickness of 0.01-0.1 mm.
14. The high-temperature resistant component according to claim 13 , wherein the thermal barrier layer contains zirconia.
15. The high-temperature resistant component according to claim 13 , wherein the environmental barrier layer has a thickness of 0.05-0.1 mm.
16. The high-temperature resistant component according to claim 13 , wherein the environmental barrier layer has a porosity of 5% or less.
17. The high-temperature resistant component according to claim 13 , wherein the thermal barrier layer has a thickness of 0.1-1 mm.
18. The high-temperature resistant component according to claim 13 , wherein the thermal barrier layer has a porosity of 10-30%.
19. The high-temperature resistant component according to claim 13 , wherein the environmental barrier layer is formed using a solution containing a silica precursor.
20. A gas turbine hot part using the high-temperature resistant component according to claim 13 .
21. The gas turbine hot part according to claim 20 , wherein the gas turbine hot part is a bucket.
22. The gas turbine hot part according to claim 20 , wherein the gas turbine hot part is used in a corrosive environment with use of low-grade oil.