Compositions and methods of deposition of thick environmental barrier coatings on CMC blade tips
Coating systems are provided for use on a CMC substrate, that can include: a bond coat on a surface of the CMC substrate; a first rare earth silicate coating on the bond coat; a sacrificial coating of a reinforced rare earth silicate matrix on the at least one rare earth silicate layer; a second rare earth silicate coating on the sacrificial coating; and an outer layer on the second rare earth silicate coating. The first rare earth silicate coating comprises at least one rare earth silicate layer, and the second rare earth silicate coating comprises at least one rare earth silicate layer. The sacrificial coating has a thickness of about 4 mils to about 40 mils. Methods are also provided for tape deposition of a sacrificial coating on a CMC substrate.
1. A coating system on an airfoil formed of a ceramic matrix composite (CMC) and defining a blade tip, the coating system comprising:
a bond coat on a surface of the airfoil;
a first rare earth silicate coating on the bond coat, wherein the first rare earth silicate coating comprises at least one rare earth silicate layer;
a sacrificial coating of a reinforced rare earth silicate matrix on the blade tip and over the at least one rare earth silicate layer;
a second rare earth silicate coating on the sacrificial coating where the sacrificial coating is present and on the first rare earth silicate coating where the sacrificial coating is not present, wherein the second rare earth silicate coating is merged with the first rare earth silicate coating where the sacrificial coating is not present to form a rare earth silicate coating that surrounds the sacrificial coating at the blade tip such that the sacrificial coating is completely encased within the first rare earth silicate coating and the second rare earth silicate coating at the blade tip; and
an outer layer on the second rare earth silicate coating.
2. The coating system of claim 1 , wherein the first rare earth silicate coating and the second rare earth silicate coating have a substantially identical composition.
3. The coating system of claim 1 , wherein the sacrificial coating has a thickness of about 8 mils to about 25 mils.
4. The coating system as in claim 1 , wherein the airfoil is a turbine blade comprising:
a shank defining a dovetail; and
a platform separating the airfoil from the shank.
5. A coating system on a blade tip of an airfoil formed of a ceramic matrix composite (CMC), the coating system comprising:
a bond coat on a surface of the airfoil;
a first rare earth silicate coating on the bond coat, wherein the first rare earth silicate coating comprises at least one rare earth silicate layer;
a sacrificial coating of a reinforced rare earth silicate matrix on the blade tip and over the at least one rare earth silicate layer, wherein the sacrificial coating has a thickness of about 4 mils to about 40 mils, and wherein a porosity in the sacrificial coating is less than 10 volume %;
a second rare earth silicate coating on the sacrificial coating where the sacrificial coating is present at the blade tip and on the first rare earth silicate coating where the sacrificial coating is not present, wherein the second rare earth silicate coating comprises at least one rare earth silicate layer, and wherein the first rare earth silicate coating and the second rare earth silicate coating are merged where the sacrificial coating is not present to surround the sacrificial coating at the blade tip such that the sacrificial coating is completely encased within the first rare earth silicate coating and the second rare earth silicate coating at the blade tip; and
an outer layer on the second rare earth silicate coating.
6. The coating system of claim 5 , wherein the sacrificial coating has a thickness of about 8 mils to about 25 mils.
7. The coating system of claim 5 , wherein the sacrificial coating has a thickness of about 16 mils to about 24 mils.
8. The coating system of claim 5 , wherein the reinforced rare earth silicate matrix comprises a rare earth silicate mixed with a discontinuous phase of barium strontium aluminosilicate.
9. The coating system of claim 8 , wherein the discontinuous phase of barium strontium aluminosilicate comprises coarse particles having an average particle size of about 5 microns to about 100 microns.
10. The coating system of claim 5 , wherein the reinforced rare earth silicate matrix comprises a rare earth silicate mixed with a discontinuous phase of silicon metal particles.
11. The coating system of claim 5 , wherein the reinforced rare earth silicate matrix comprises a rare earth disilicate.
12. The coating system of claim 5 , wherein the reinforced rare earth silicate matrix comprises a rare earth monosilicate.
13. The coating system of claim 5 , wherein the reinforced rare earth silicate matrix comprises a mixture of a rare earth monosilicate and a rare earth disilicate.
14. The coating system of claim 5 , wherein the bond coat is a silicon bond coat.
15. The coating system of claim 5 , wherein the first rare earth silicate coating and the second rare earth silicate coating have a substantially identical composition.
16. The coating system as in claim 5 , wherein the airfoil is a turbine blade comprising:
a shank defining a dovetail; and
a platform separating the airfoil from the shank.