Abradable layer including a rare earth silicate
An abradable coating may include a rare earth silicate. The abradable coating may be deposited over a substrate, an environmental barrier coating, or a thermal barrier coating. The abradable coating may be deposited on a gas turbine blade track or a gas turbine blade shroud to form a seal between the gas turbine blade track or gas turbine blade shroud and a gas turbine blade. The abradable coating may also include a plurality of layers, such as alternating first and second layers including, respectively, a rare earth silicate and stabilized zirconia or stabilized hafnia.
1. A system comprising:
a blade track or blade shroud comprising:
a substrate,
an environmental barrier coating (EBC) formed over the substrate, wherein the EBC comprises at least one of mullite, barium strontium alumina silicate, barium alumina silicate, calcium alumina silicate, strontium alumina silicate, lithium alumina silicate, magnesium alumina silicate, or a rare earth silicate, and
a multilayer, porous abradable coating formed over the EBC, wherein the multilayer, porous abradable coating comprises a plurality of layer pairs, and wherein each layer pair comprises a first layer including a rare earth silicate and a second layer including at least one of stabilized zirconia and stabilized hafnia; and
a gas turbine blade comprising a blade tip, wherein the blade track or blade shroud and the gas turbine blade are configured so the blade tip contacts a portion of the multilayer, porous abradable coating during rotation of the gas turbine blade, and wherein the multilayer, porous abradable coating is configured to be abraded by the contact by the blade tip.
2. The system of claim 1 , wherein the environmental barrier coating comprises a rare earth silicate.
3. The system of claim 1 , wherein at least one of the first layers of the multilayer, porous abradable coating comprises at least one of RE 2 SiO 5 and RE 2 Si 2 O 7 , and wherein RE is a rare earth element.
4. The system of claim 1 , wherein at least one of the first layers of the multilayer, porous abradable coating further comprises a rare earth oxide.
5. The system of claim 1 , wherein at least one of the first layers of the multilayer, porous abradable coating further comprises silica.
6. The system of claim 1 , wherein at least one of the first layers of the multilayer, porous abradable coating further comprises at least one of alumina, Ta 2 O 5 , HfSiO 4 , an alkali oxide, and an alkali earth oxide.
7. The system of claim 1 , wherein the multilayer, porous abradable coating comprises a first surface adjacent the environmental barrier coating (EBC) and a second surface opposite the EBC, and wherein a first porosity of the multilayer, porous abradable coating proximate the first surface is different from a second porosity of the multilayer, porous abradable coating proximate the second surface.
8. The system of claim 7 , wherein the first porosity is less than the second porosity.
9. The system of claim 1 , wherein the substrate comprises a ceramic matrix composite.
10. The system of claim 9 , further comprising a bond coat including at least one of mullite, silica, a silicide, or silicon, wherein the environmental barrier layer is formed over the bond coat.
11. The system of claim 1 , wherein the substrate comprises a superalloy.
12. The system of claim 11 , further comprising a bond coat including at least one of an MCrAlY alloy, a β-NiAl nickel aluminide alloy, or a γ-Ni+γ′-Ni 3 Al nickel aluminide alloy, wherein the environmental barrier layer is formed over the bond coat.
13. The system of claim 1 , further comprising a thermal barrier coating (TBC) comprising zirconia or hafnia, wherein the environmental barrier coating is formed over the TBC.
14. The system of claim 1 , further comprising a thermal barrier coating (TBC) comprising zirconia or hafnia, wherein the TBC is formed over the environmental barrier coating, and wherein the multilayer, porous abradable coating is formed over the TBC.