MACHINABLE COATING FOR DAMPING

20240271537

18/169176

February 14, 2023

A gas turbine engine blade includes a platform, an airfoil section extending from the platform in a first direction, a mount extending from the platform in a second direction opposite the first direction, and a damper deposited on one of the platform, the airfoil section, and the mount. A method of sizing a damper for a gas turbine engine blade is also disclosed.

1. A gas turbine engine blade, comprising: a platform; an airfoil section extending from the platform in a first direction; a mount extending from the platform in a second direction opposite the first direction; and a damper deposited on one of the platform, the airfoil section, and the mount.

2. The gas turbine engine blade of claim 1, wherein the damper is machinable.

3. The gas turbine engine blade of claim 2, wherein the damper includes at least one of rare earth silicates, alkaline earth silicates, alkaline earth aluminosilicates, yttria-stabilized zirconia, alumina-stabilized zirconia, mullite, titania, chromia, silicon, silicon oxides, silicon carbides, silicon oxycarbides, silicon nitride, silicon-aluminum-oxygen-nitrogen, barium-magnesium aluminosilicate, hafnium oxides such as hafnon, hafnium silicon oxides, alumina-stabilized zirconia, zirconium oxides such as zircon, yttrium oxides such as yttria, and combinations thereof.

4. The gas turbine engine blade of claim 3, wherein the damper includes at least one of hafnon, zircon, and mullite.

5. The gas turbine engine blade of claim 1, wherein the blade is one of a ceramic matrix composite blade or a monolithic ceramic blade.

6. The gas turbine engine blade of claim 1, wherein the damper is on the platform.

7. The gas turbine engine blade of claim 6, wherein the damper is on a non-gas-path surface of the platform.

8. The gas turbine engine blade of claim 1, wherein the blade comprises a ceramic matrix composite.

9. The gas turbine engine blade of claim 1, wherein the blade comprises a monolithic ceramic material.

10. The gas turbine engine blade of claim 1, where there are no fasteners attaching the damper to the blade.

11. A method of sizing a damper for a gas turbine engine blade, comprising: determining the mass of a blade; depositing a damper onto the blade; determining a mass of the damper after the depositing step; and machining the damper to remove mass.

12. The method of claim 11, further comprising comparing a mass of the damper to a desired mass.

13. The method of claim 12, further comprising repeating the machining step if the mass of the damper is larger than the desired mass.

14. The method of claim 11, wherein the depositing is by at least one of plasma spray, slurry coating, chemical vapor deposition (CVD), physical vapor deposition, and electron beam physical deposition

15. The method of claim 11, wherein the machining is by grinding, ultrasonic machining, water guided laser, milling, or reaming.

16. The method of claim 11, wherein the blade is one of a ceramic matrix composite blade or a monolithic ceramic blade.

17. The method of claim 11, wherein the deposition attaches the damper to the blade without any fasteners.

18. The method of claim 11, wherein the blade includes an airfoil section, a platform, and a mount, and wherein the damper is deposited onto the platform.

19. The method of claim 18, wherein the damper is deposited onto a non-gas-path surface of the platform.

20. The method of claim 11, wherein the damper includes at least one of rare earth silicates, alkaline earth silicates, alkaline earth aluminosilicates, yttria-stabilized zirconia, alumina-stabilized zirconia, mullite, titania, chromia, silicon, silicon oxides, silicon carbides, silicon oxycarbides, silicon nitride, silicon-aluminum oxygen-nitrogen, barium-magnesium aluminosilicate, hafnium oxides such as hafnon, hafnium silicon oxides, alumina-stabilized zirconia, zirconium oxides such as zircon, yttrium oxides such as yttria, and combinations thereof.

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edspap.20240271537