Tubine engine component having wear coating and method for coating a turbine engine component
AssigneeGeneral Electric Company
InventorsWAYNE CHARLES HASZ, DAVID EDWARD BUDINGER
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Abstract
A turbine engine component includes a substrate and a wear coating on the substrate. The wear coating includes wear-resistant particles in a matrix phase, the wear-resistant particles being formed of chrome carbide or a cobalt alloy. Methods for forming a turbine engine component are also disclosed.
Claims44
A turbine engine component comprising:
- a substrate;
- and
- a wear coating on the substrate, the wear coating comprising wear-resistant particles in a matrix phase, the wear-resistant particles comprising a material from the group consisting of chrome carbide and a cobalt alloy.
A method for coating a substrate, comprising the steps of:
- providing a substrate;
- applying braze alloy and wear-resistant particles on the substrate, the wear-resistant particles comprising a material from the group consisting of chrome carbide and a cobalt alloy;
- and
- heating the braze alloy to bond the wear-resistant particles to the substrate to form a wear coating on the substrate.
A method for coating a substrate, comprising the steps of:
- providing a substrate;
- attaching a preform to the substrate, the preform containing braze alloy and wear-resistent particles;
- and
- heating the preform to form a wear-resistant coating.
A turbine engine component comprising:
- a substrate;
- and
- a wear coating on the substrate, the wear coating comprising wear-resistant particles in a matrix phase, the wear-resistant particles comprising a material from the group consisting of
- (i) Cr23C6, Cr7C3, Cr3C2, and combinations thereof, and
- (ii) a cobalt alloy, wherein said cobalt alloy forms a lubricious oxide film, and the matrix phase comprising a nickel-base or a cobalt-base alloy, wherein nickel or cobalt is the single greatest element of the alloy by weight, wherein
- the turbine engine component is selected from the group consisting of a nozzle, shroud, shroud hanger, pressure balance seal, and combuster component.
A method for coating a turbine engine component, comprising the steps of:
- providing a substrate, the substrate being selected from the group consisting of a nozzle, shroud, shroud hanger, pressure balance seal, and combustor component;
- applying braze alloy and wear-resistant particles on the substrate, the braze alloy comprising a nickel-base or a cobalt-base alloy, wherein nickel or cobalt is the single greatest element of the alloy by weight, and the wear-resistant particles comprising a material from the group consisting of
- (i) Cr23C6, Cr7C3, Cr3C2, and combinations thereof, and
- (ii) a cobalt alloy, wherein said cobalt alloy forms a lubricious oxide film;
- and
- heating the braze alloy to bond the wear-resistant particles to the substrate to form a wear coating on the substrate.
A method for coating a turbine engine component, comprising the steps of:
- providing a substrate, the substrate being selected from the group consisting of a nozzle, shroud, shroud hanger, pressure balance seal, and combustor component;
- attaching a preform to the substrate, the preform containing braze alloy and wear-resistant particles, the braze alloy comprising a nickel-base or a cobalt-base alloy, wherein nickel or cobalt is the single greatest element of the alloy by weight, and the wear-resistant particles comprising a material from the group consisting of
- (i) Cr23C6, Cr7C3, Cr3C2, and combinations thereof, and
- (ii) a cobalt alloy, wherein said cobalt alloy forms a lubricious oxide film;
- and
- heating the preform to form a wear-resistant coating.
Dependencies are inferred from the claim text.