Ceramic coating material
A ceramic material suitable for use as a coating, such as a porous thermal barrier coating (TBC) on a component intended for use in a hostile thermal environments. The coating material consists essentially of zirconia stabilized by at least one rare-earth metal oxide and further alloyed to contain a limited amount of titania. Rare-earth metal oxides of particular interest are lanthana, ceria, neodymia, europia, gadolinia, erbia, dysprosia, and ytterbia, individually or in combination. Zirconia, the rare-earth metal oxide, and titania are present in the coating material in amounts to yield a predominantly tetragonal phase crystal structure. The amount of titania in the coating is tailored to allow higher levels of stabilizer while maintaining the tetragonal phase, i.e., avoiding the cubic (fluorite) phase.
1. A component comprising a ceramic coating formed of an unsintered ceramic material having a porous microstructure and consisting of zirconia, about 2 to about 20 weight percent of at least one rare earth metal oxide as a stabilizer, about 0.5 to about 10 weight percent titania, and optionally up to about 8 weight percent yttria, the rare earth metal oxide and the titania being present in amounts to achieve a predominantly tetragonal crystal phase in the coating, wherein:
the at least one rare-earth metal oxide is chosen from the group consisting of lanthana, ceria, neodymia, europia, gadolinia, erbia, dysprosia, and ytterbia; and either
the ceramic material consists of zirconia, titania, and at least one of lanthana, ceria, neodymia, europia, gadolinia, and ytterbia as the at least one rare-earth metal oxide; or
the ceramic material consists of zirconia, titania, at least one of lanthana, ceria, dysprosia, erbia and ytterbia as the at least one rare-earth metal oxide, and optionally yttria.
2. A component comprising a ceramic coating formed of an unsintered ceramic material having a porous microstructure and consisting of zirconia, about 2 to about 20 weight percent of one rare earth metal oxide chosen from the group consisting of oxides of lanthanum, cerium, neodymium, europium, gadolinium, erbium, dysprosium, and ytterbium, and about 0.5 to about 10 weight percent titania, the rare earth metal oxide and the titania being present in amounts to achieve a predominantly tetragonal crystal phase in the coating.
3. The component according to claim 2 , wherein the ceramic material contains 6 to 14 weight percent of the rare-earth metal oxide.
4. The component according to claim 2 , wherein the ceramic material contains 6 to 12 weight percent of the rare-earth metal oxide.
5. The component according to claim 2 , wherein the ceramic material contains up to 6 weight percent titania.
6. The component according to claim 2 , wherein the ceramic material contains 2 to 3 weight percent titania.
7. The component according to claim 2 , wherein the component is a gas turbine engine component.
8. A gas turbine engine component comprising:
a superalloy substrate;
a metallic bond coat on a surface of the substrate; and
a thermal barrier layer as an outermost coating of the component, the thermal barrier layer being formed by an unsintered ceramic material having a porous microstructure of columnar grains and a predominantly tetragonal crystal structure, the ceramic material consisting of zirconia, one rare earth metal oxide in an amount of 2 to 20 weight percent, and 0.5 to 10 weight percent titania, the rare-earth metal oxide being chosen from the group consisting of lanthana, ceria, neodymia, europia, gadolinia, erbia, dysprosia, and ytterbia.
9. The gas turbine engine component according to claim 8 , wherein the rare-earth metal oxide is lanthana.
10. The gas turbine engine component according to claim 8 , wherein the rare-earth metal oxide is ceria.
11. The gas turbine engine component according to claim 8 , wherein the rare-earth metal oxide is neodymia.
12. The gas turbine engine component according to claim 8 , wherein the rare-earth metal oxide is europia.
13. The gas turbine engine component according to claim 8 , wherein the rare-earth metal oxide is gadolinia.
14. The gas turbine engine component according to claim 8 , wherein the rare-earth metal oxide is erbia.
15. The gas turbine engine component according to claim 8 , wherein the rare-earth metal oxide is dysprosia.
16. The gas turbine engine component according to claim 8 , wherein the rare-earth metal oxide is ytterbia.
17. The gas turbine engine component according to claim 8 , wherein the ceramic material contains up to 2 weight percent titania.
18. The gas turbine engine component according to claim 8 , wherein the ceramic material contains 2 to 3 weight percent titania.
19. The gas turbine engine component according to claim 8 , wherein the ceramic material contains 6 to 12 weight percent of the rare-earth metal oxide.