Abstract: Methods for producing a high temperature oxidation and hot corrosion resistant MCrAlX coating on a superalloy substrate include applying an M-metal, chromium, and aluminum or an aluminum alloy comprising a reactive element to at least one surface of the superalloy component by electroplating at electroplating conditions below 100° C. in a plating bath thereby forming a plated component and heat treating the plated component.

Abstract: Substantially defect-free titanium aluminide components and methods are provided for manufacturing the same from articles formed by consolidation processes. The method includes providing an intermediate article comprised of a titanium aluminide alloy and formed by a consolidation process. The intermediate article is encapsulated with an aluminum-containing encapsulation layer. The intermediate article is compacted after the encapsulation step. A substantially defect-free titanium aluminide component comprises a compacted three-dimensional article comprised of titanium aluminide and formed by a consolidation process and an aluminum-containing encapsulation layer on at least one surface of the compacted three-dimensional article. The aluminum-containing encapsulation layer comprises an aluminide material, MCrAlY wherein M is cobalt, nickel, or a combination of cobalt and nickel, or TiAlCr.

Abstract: Methods for producing a high temperature oxidation resistant coating on a superalloy component and the coated superalloy component produced thereby are provided. Aluminum or an aluminum alloy is applied to at least one surface of the superalloy component by electroplating in an ionic liquid aluminum plating bath to form a plated component. The plated component is heat treated at a first temperature of about 600° C. to about 650° C. and then further heat treated at a second temperature of about 700° C. to about 1050° C. for about 0.50 hours to about two hours or at a second temperature of about 750° C. to about 900° C. for about 12 to about 20 hours.

Abstract: Substantially defect-free titanium aluminide components and methods are provided for manufacturing the same from articles formed by consolidation processes. The method includes providing an intermediate article comprised of a titanium aluminide alloy and formed by a consolidation process. The intermediate article is encapsulated with an aluminum-containing encapsulation layer. The intermediate article is compacted after the encapsulation step. A substantially defect-free titanium aluminide component comprises a compacted three-dimensional article comprised of titanium aluminide and formed by a consolidation process and an aluminum-containing encapsulation layer on at least one surface of the compacted three-dimensional article. The aluminum-containing encapsulation layer comprises an aluminide material, MCrAlY wherein M is cobalt, nickel, or a combination of cobalt and nickel, or TiAlCr.

Abstract: Methods for producing a high temperature oxidation and hot corrosion resistant MCrAlX coating on a superalloy substrate include applying an M-metal, chromium, and aluminum or an aluminum alloy comprising a reactive element to at least one surface of the superalloy component by electroplating at electroplating conditions below 100° C. in a plating bath thereby forming a plated component and heat treating the plated component.

Abstract: Methods for producing a high temperature oxidation resistant coating on a superalloy component and the coated superalloy component produced thereby are provided. Aluminum or an aluminum alloy is applied to at least one surface of the superalloy component by electroplating in an ionic liquid aluminum plating bath to form a plated component. The plated component is heat treated at a first temperature of about 600° C. to about 650° C. and then further heat treated at a second temperature of about 700° C. to about 1050° C. for about 0.50 hours to about two hours or at a second temperature of about 750° C. to about 900° C. for about 12 to about 20 hours.

Abstract: Methods are provided for forming coatings on substrates. In an embodiment, a method includes forming a first metal layer on the substrate, the first metal layer comprising a first precious metal, electrodepositing an active element over the first metal layer to form an active element layer, the active element selected from the group consisting of yttrium, scandium, and a lanthanide series element, applying a second metal layer over the active element layer, the second metal layer consisting essentially of a metal selected from a group consisting of a second precious metal, nickel, and cobalt, heating the substrate including the first metal layer, the active element layer, and the second metal layer to form a diffusion-alloyed layer over the substrate, adding aluminum to the diffusion-alloyed layer, and heating the substrate to diffuse and react the aluminum with the diffusion-alloyed layer to form a modified precious metal aluminide coating on the substrate.

Abstract: A quasi-single phase or single phase thick platinum nickel aluminide coating and methods for forming the coating over a nickel-based superalloy substrate are provided. The method includes the steps of forming a metal layer over a surface of the nickel-based superalloy substrate, the metal layer comprising platinum, growing a diffusion zone comprising a platinum nickel alloy layer from the metal layer and the nickel-based superalloy substrate, and subjecting the platinum nickel alloy to one or more aluminization cycles to transform the platinum nickel alloy into a platinum nickel aluminide coating having a platinum aluminide phase formed therein.

Abstract: The present invention provides a chromium and active elements modified platinum aluminide coating that may be used on a surface of a gas turbine engine component such as a turbine blade. The coating may be used as a protective coating that impedes the progress of corrosion, oxidation, and sulfidation in superalloy materials that comprise the substrate of the turbine blade. Additionally, the coating may be used as a bond coat onto which a thermal barrier coating is deposited. The presence of active elements as well as chromium and platinum provides improved corrosion, oxidation, and sulfidation resistance. The coating is applied using an electron beam physical vapor deposition. The coating is applied alternatively using selected sequential diffusion processing steps involving chromium, platinum and aluminum.

Abstract: The present invention provides a chromium and active elements modified platinum aluminide coating that may be used on a surface of a gas turbine engine component such as a turbine blade. The coating may be used as a protective coating that impedes the progress of corrosion, oxidation, and sulfidation in superalloy materials that comprise the substrate of the turbine blade. Additionally, the coating may be used as a bond coat onto which a thermal barrier coating is deposited. The presence of active elements as well as chromium and platinum provides improved corrosion, oxidation, and sulfidation resistance. The coating is applied using an electron beam physical vapor deposition. The coating is applied alternatively using selected sequential diffusion processing steps involving chromium, platinum and aluminum.

Abstract: There is provided a method for applying a diffusion coating on a specific area of targeted industrial item such as a turbine blade. The method uses a covering material such as a tape or slurry to cover the area where it is desired that the diffusion occur, for example above the root area of a turbine blade. The tape material includes a metallic source such as chromium and a master alloy of active elements for diffusion. The covering material thus defines the localized patch that is to be coated. An activator if any, such as a halide activator, can be included in the tape or slurry. Alternatively, the activator can be included in the pack material. The method uses known pack cementation methods to complete the diffusive process. The method results in a diffusion coating over a specific area of the target item.