Abstract: A method includes applying a material coating to a surface of a machine component, wherein the material coating is formed from a combination of a hardfacing material, aluminum-containing particles, and a braze material. The method also includes thermally treating the material coating at a temperature to generate an oxide layer comprising aluminum from the aluminum-containing particles, wherein the oxide layer is configured to reduce oxidation of the hardfacing material, and the braze material is configured to facilitate binding between the material coating and the surface of the machine component.

Abstract: A method of forming a component. The method includes applying a thermal barrier coating to the component to facilitate decreasing heat transfer to the component, wherein the thermal barrier coating includes at least one thermal insulating layer and a metallic bond coat layer in contact with an outer surface of the component. The method also includes forming a plurality of grooves in the at least one thermal insulating layer of the thermal barrier coating to facilitate increasing a strain tolerance of the thermal barrier coating, wherein each of the plurality of grooves extends a depth into the at least one thermal insulating layer. The method further includes depositing a material within the plurality of grooves to facilitate increasing an amount of thermal protection of the metallic bond coat layer within those areas of the thermal barrier coating in which the plurality of grooves are formed.

Abstract: A method of manufacturing a target component is disclosed. The method includes inputting, into a binder jetting additive manufacturing system, instructions for manufacturing a desired target component, wherein the target component includes at least one internal channel defined at least by a circuitous path including at least one bend; printing the target component via a binder jet additive manufacturing process to form a green body target component, wherein during the printing at least one port is formed that extends from an external surface of the target component to the at least one internal channel; and depowdering the at least one internal channel by accessing the at least one port formed on the green body target component.

Abstract: A method includes applying a material coating to a surface of a machine component, wherein the material coating is formed from a combination of a hardfacing material, aluminum-containing particles, and a braze material. The method also includes thermally treating the material coating at a temperature to generate an oxide layer comprising aluminum from the aluminum-containing particles, wherein the oxide layer is configured to reduce oxidation of the hardfacing material, and the braze material is configured to facilitate binding between the material coating and the surface of the machine component.

Abstract: A method includes applying a material coating to a surface of a machine component, wherein the material coating is formed from a combination of a hardfacing material, aluminum-containing particles, and a braze material. The method also includes thermally treating the material coating at a temperature to generate an oxide layer comprising aluminum from the aluminum-containing particles, wherein the oxide layer is configured to reduce oxidation of the hardfacing material, and the braze material is configured to facilitate binding between the material coating and the surface of the machine component.

Abstract: A method includes applying a material coating to a surface of a machine component, wherein the material coating is formed from a combination of a hardfacing material, aluminum-containing particles, and a braze material. The method also includes thermally treating the material coating at a temperature to generate an oxide layer comprising aluminum from the aluminum-containing particles, wherein the oxide layer is configured to reduce oxidation of the hardfacing material, and the braze material is configured to facilitate binding between the material coating and the surface of the machine component.

Abstract: A method of manufacturing specialized alloys having specific properties and an alloy made using this method. The methods involve the use of micro and/or nano-sized particles that are mixed into an alloy using a friction stir welding method. The micro and/or nano-sized particles are used to alter one or more characteristics of the alloy in the locations in which the micro and/or nano-sized particles are added. The micro and/or nano-sized particles may be metal particles, non-metal particles, or a combination thereof.

Abstract: A method of adding material to a nickel-based superalloy component, such as a gas turbine rotor disk, without damaging the underlying material and without creating an unacceptable level of cracking. The method is advantageously applied in the repair of Alloy 706 turbine rotors having experienced operating failures in the steeple region of the disk. Once the damaged material is removed, replacement nickel-based superalloy material is added using a welding process that protects both the underlying material and the replacement material. The replacement material may be added by welding, with the preheat temperature maintained no lower than 100° C. below the aging temperature of the deposited alloy and with the interpass temperature maintained below the solution annealing temperature of the alloy. Alternatively, the replacement material may be preformed and welded to the original material using a friction welding process.

Abstract: A method of welding alloys having directionally-solidified grain structure. The methods improve the weldability of these alloys by creating a localized region of fine grain structure, wherein the welding occurs in these localized regions. The localized regions are formed by applying strain energy using a variety of different methods, such as by hammer peening, laser peening or sand blasting. Then, a heat treatment step may be used to create recrystallized grains having the fine grain structure. The region of fine grain structure provides better weldability.

Abstract: An improved method of heat treating superalloys prior to welding includes subjecting only the portion of the component to be repaired to a localized heat treatment, leaving the remainder of the component untreated. The localized heat treatment permits the use of higher hold temperatures that are near, at, or above the Ni3(Al,Ti) solution temperature of the alloy. Such heat treatment prevents strain age cracking and also prevents recrystallization in areas that are not heat treated. Such localized heat treatment can be applied before and/or after welding, for material rejuvenation, pre-brazing, and post-brazing.

Abstract: A method of welding superalloy components comprising: pre-heat one or more components to be welded to a temperature of at least 1500° F. in a substantially enclosed inert gas atmosphere; supplying multiple fillers to the weld zone, at least two of said fillers having different compositions; and welding the one or more preheated components utilizing a laser beam, while maintaining said pre-heat temperature.

Abstract: A method of repairing a combustion turbine component having damage located at or near a cooling hole or hollow or geometrically complex portion of the component is provided. The method comprises forming a preparatory groove that extends from a surface of the component to the damaged area but does not extend to the cooling hole or hollow or geometrically complex portion of the component, the groove extending 40–90% the distance from the component to the damaged area; spraying a filler material into the groove with a micro-plasma torch at a current of less than 50 amperes; and filling the groove with the filler material such that the heated filler material substantially extends from the cooling hole or hollow or geometrically complex portion of the component to a surface of the component.