A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A meter section of a cooling aperture is formed in the substrate. An internal coating is applied onto a surface of the meter section. An external coating is applied over the substrate. A diffuser section of the cooling aperture is formed in the external coating and the substrate to provide the cooling aperture.

A method of treating the surface of a 3D object, comprising obtaining a digital 3D shape representation defining characteristics of the object; using a computerised device to convert the 3D shape representation into a digital 2D shape representation defining the 3D surface of the object as it if laid out flat; using the computerised device to generate a digital 2D tool path representation defining movements an applicator or removal tool would take to treat the surface of the shape defined by the 2D shape representation; using the computerised device to convert the 2D tool path representation to a digital 3D tool path representation defining movements that the applicator or removal tool will take to deposit material on, or remove it from, the surface to treat the 3D object; and using the 3D tool path representation to control the applicator tool or removal tool to treat the 3D object.

The present disclosure relates generally to a fixture for use in applying a coating to a multiple vane nozzle for use in a turbomachine. The fixture includes first and second masks that are applied to opposite sides of the nozzle to mimic the geometry and spacing of the vanes of the nozzle.

The present disclosure relates generally to a fixture for use in applying a coating to a multiple vane nozzle for use in a turbomachine. The fixture includes first and second masks that are applied to opposite sides of the nozzle to mimic the geometry and spacing of the vanes of the nozzle.

A turbine component surface treatment process includes passing a UV-curable maskant through one or more fluid flow passages, wherein at least a portion of the UV-curable maskant exits the one or more fluid flow passages at an exterior surface of the turbine component, applying a UV light to the exterior surface of the turbine component, wherein the UV light cures at least a portion of the UV-curable maskant exiting the one or more fluid flow passages, and, treating the exterior surface with a treatment material, wherein the portion of the UV-curable maskant cured by the UV light substantially blocks the treatment material from entering the one or more fluid flow passages.

A turbine component surface treatment process includes passing a UV-curable maskant through one or more fluid flow passages, wherein at least a portion of the UV-curable maskant exits the one or more fluid flow passages at an exterior surface of the turbine component, applying a UV light to the exterior surface of the turbine component, wherein the UV light cures at least a portion of the UV-curable maskant exiting the one or more fluid flow passages, and, treating the exterior surface with a treatment material, wherein the portion of the UV-curable maskant cured by the UV light substantially blocks the treatment material from entering the one or more fluid flow passages.

A method of improving a structure of a component adjacent a feature is provided including removing a portion of the structure including at least one area where damage of corrosion has occurred or is likely to occur to expose a surface of the structure. A masking plug is installed into the feature such that a base of the masking plug is coupled to a first portion of the feature and a head of the masking plug is arranged adjacent a second portion of the feature. A structural deposit is formed on the surface and is integral with the structure. Excess material of the structural deposit and a portion of the head of the masking plug is removed. The second portion of the feature is reformed and the masking plug is removed from the feature.

An article has a metallic substrate having a plurality of recesses. A first coating is at least at the recesses and has: a splatted layer; and a columnar layer atop the splatted layer. A second coating is away from the recesses and has: a columnar layer atop the substrate without an intervening splatted layer.

An article has a metallic substrate having a plurality of recesses. A first coating is at least at the recesses and has: a splatted layer; and a columnar layer atop the splatted layer. A second coating is away from the recesses and has: a columnar layer atop the substrate without an intervening splatted layer.

A thermal coating method for applying a functional layer to a workpiece surface, particularly for applying a running surface coating to a cylinder running surface of a crankcase of an internal-combustion engine, includes the steps of: melting a coating material by use of a melting device, applying coating material droplets to the workpiece surface by use of a gas jet aimed at the workpiece surface, which gas jet blows coating material droplets from a melting location of the melting device onto the workpiece surface, and cooling or rapidly freezing the coating material droplets during their transport from the melting location to the workpiece surface.