Abstract: An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.

Abstract: A method of forming a ferrous metal case-hardened layer using additive manufacturing. The method includes delivering, by a material delivery device, a filler material to a surface of a substrate. The substrate includes a first ferrous metal. The filler material includes a second ferrous metal and a carbon-based material. The method also includes directing, by an energy delivery device, an energy toward a volume of the filler material to join at least some of the filler material to the substrate to form a component.

Abstract: In some examples, a method for additive manufacturing an article, the method including depositing a filament via a filament delivery device to form at least one track of the deposited filament, the at least one track of the deposited filament forming at least a portion of a preform article, wherein the filament includes a sacrificial binder and a powder, wherein the powder includes a plurality of elongated particles with each respective particle defining a longitudinal axis, wherein the longitudinal axes of the plurality of particles are substantially aligned with each other within the at least one track of the deposited filament; removing substantially all the binder from the at least one track of the preform article to form a powder article; and sintering the powder article to form a sintered article.

Abstract: An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.

Abstract: An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.

Abstract: In some examples, a method for additive manufacturing an article, the method including depositing a filament via a filament delivery device to form at least one track of the deposited filament, the at least one track of the deposited filament forming at least a portion of a preform article, wherein the filament includes a sacrificial binder and a powder, wherein the powder includes a plurality of elongated particles with each respective particle defining a longitudinal axis, wherein the longitudinal axes of the plurality of particles are substantially aligned with each other within the at least one track of the deposited filament; removing substantially all the binder from the at least one track of the preform article to form a powder article; and sintering the powder article to form a sintered article.

Abstract: An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.

Abstract: An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.

Abstract: A method of forming a ferrous metal case-hardened layer using additive manufacturing. The method includes delivering, by a material delivery device, a filler material to a surface of a substrate. The substrate includes a first ferrous metal. The filler material includes a second ferrous metal and a carbon-based material. The method also includes directing, by an energy delivery device, an energy toward a volume of the filler material to join at least some of the filler material to the substrate to form a component.

Abstract: An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.