Continuous fiber reinforced mesh bond coat for environmental barrier coating system
A gas turbine blade may have a bond coat applied to its surface. A porous substrate may be applied to the bond layer and one or more protective layers may be applied to the bond layer such that the fiber mesh is embedded between the bond layer and the protective layer to prevent creep.
1. A coated gas turbine blade with reduced creep between layers, the blade comprising:
a surface;
a bond layer applied to the surface;
a porous substrate applied to the bond layer;
a fiber mesh; and
a protective layer;
the fiber mesh being embedded between the bond layer and the protective layer when the protective layer is applied to the bond layer with the fiber layer therebetween, wherein the fiber mesh of the porous substrate mitigates creep between the bond layer and protective layer.
2. The gas turbine blade of claim 1 , wherein the protective layer comprises at least one environmental barrier coating.
3. The gas turbine blade of claim 1 , wherein the gas turbine blade is configured to provide at least one expected direction of creep, and wherein at least some fibers of the fiber mesh are oriented perpendicular to the at least one expected direction of creep.
4. The gas turbine blade of claim 1 , wherein the fiber mesh comprises fibers made from at least one of single oxides, carbides, nitrides, intermetallic, and a combination thereof.
5. The gas turbine blade of claim 1 , wherein the fiber mesh is applied to a first section of the surface and not applied to a second section of the surface.
6. The gas turbine blade of claim 1 , wherein the porous substrate comprises woven fibers.
7. The gas turbine blade of claim 1 , wherein the porous substrate comprises a mesh of continuous ceramic fibers.
8. The gas turbine blade of claim 1 , wherein the porous substrate is applied to the entirety of the surface.
9. The gas turbine blade of claim 1 , wherein the porous substrate comprises fibers made from a single crystal for of an oxide fiber.
10. A method of forming a coated gas turbine blade with reduced creep between layers, the method comprising:
applying a bond layer to a surface of a gas turbine blade;
preparing a porous substrate by at least one of partially or completely embedding a fiber mesh in the porous substrate;
applying the porous substrate to the bond layer with the fiber layer therebetween; and
applying a protective layer to the bond layer such that the fiber mesh is embedded between the bond layer and the protective layer, whereby the fiber mesh of the porous substrate mitigates creep between the bond layer and protective layer.
11. The method of claim 10 , wherein the protective layer comprises at least one environmental barrier coating.
12. The method of claim 10 , wherein the porous substrate comprises a mesh of unidirectional fibers.
13. The method of claim 10 , wherein the porous substrate comprises a mesh of woven fibers.
14. The method of claim 10 , wherein the porous substrate comprises continuous ceramic fibers.
15. The method of claim 10 , wherein gas turbine blade is configured to provide at least one expected direction of creep, and wherein the applying the porous substrate to the bond layer comprised applying a fiber mesh to the bond layer such that at least some fibers of the fiber mesh are oriented perpendicular to the at least one expected direction of creep.
16. The method of claim 10 , wherein the porous substrate comprises a fiber mesh comprising fibers made from at least one of single oxides, carbides, nitrides, intermetallic, and a combination thereof.
17. The method of claim 10 , wherein applying the porous substrate to the bond layer comprised applying the porous substrate to a first section of the surface covered by the bond layer and not applying the porous substrate to a second section of the surface covered by the bond layer.
18. The method of claim 10 , wherein applying the porous substrate to the bond layer comprised applying the porous substrate to the entirety of the surface covered by the bond layer.
19. The method of claim 10 , wherein the porous substrate comprises a fiber mesh comprising fibers made from a single crystal of an oxide fiber.
20. A coated gas turbine blade with reduced creep between layers, the blade comprising:
a surface;
a bond layer applied to the surface;
a porous substrate applied to the bond layer; the porous substrate comprising a fiber mesh; and
a protective layer;
the fiber mesh being embedded between the bond layer and the protective layer when the protective layer is applied to the bond layer with the fiber layer therebetween wherein the fiber mesh serves as anchors for the porous substrate to mitigate creep between the bond layer and protective layer, wherein the porous substrate comprises a mesh of unidirectional fibers.