Abstract: A method for forming a secondary component from an original component having an original shape includes separating the original component into a parent component and a replaced portion, and forming a replacement coupon using an additive manufacturing system. The replacement coupon is shaped to substantially match the original shape of the replaced portion. The method further includes coupling the replacement coupon to the parent component to form the secondary component. The method also includes at least one of (i) removing the replacement coupon from a build plate of the additive manufacturing system prior to application of any heat treatment to the as-built replacement coupon, wherein the replacement coupon maintains a near-net original shape of the replaced portion after removal, and (ii) entering the secondary component into normal duty with no hot isostatic press treatment of the replacement coupon having been performed.

Abstract: A component and method of forming a component are disclosed. The component includes a cast alloy section and an additive manufacturing section secured to the cast alloy section. Both the cast alloy section and the additive manufacturing section form at least a portion of an outer surface of the component. The method of forming a component includes removing a portion of an existing component, the removing of the portion forming an open section in the existing component, forming an article through an additive manufacturing technique, the article having a shape and geometry arranged and disposed to fill the open section in the existing component, and securing the article within the open section of the existing component to form the component. Another method includes directly depositing a material, by an additive manufacturing technique, over a portion of the existing component.

Abstract: A coated component and a method of preparing a coated component are provided. The method comprises providing a substrate; and applying a dual coating system to the substrate. The applying of the dual coating system includes applying a diffusion barrier coating; and applying a corrosion-resistant coating. The corrosion-resistant coating comprises a greater concentration of silicon and aluminum than the diffusion barrier coating, and the dual layer coating system includes an aluminide interdiffusion zone.

Abstract: A method for repairing a component is disclosed. The method includes removing a portion originally including a plurality of cooling holes, of the component to form a cavity, forming by additive manufacturing a replacement portion including a plurality of cooling holes, and varying a surface roughness and a diameter of at least one cooling hole of the plurality of cooling holes during the forming by additive manufacturing the replacement portion. The replacement portion replaces the portion of the component.

Abstract: A coated component and a method of preparing a coated component are provided. The method comprises providing a substrate; and applying a dual coating system to the substrate. The applying of the dual coating system includes applying a diffusion barrier coating; and applying a corrosion-resistant coating. The corrosion-resistant coating comprises a greater concentration of silicon and aluminum than the diffusion barrier coating, and the dual layer coating system includes an aluminide interdiffusion zone.

Abstract: A component and method of forming a component are disclosed. The component includes a cast alloy section and an additive manufacturing section secured to the cast alloy section. Both the cast alloy section and the additive manufacturing section form at least a portion of an outer surface of the component. The method of forming a component includes removing a portion of an existing component, the removing of the portion forming an open section in the existing component, forming an article through an additive manufacturing technique, the article having a shape and geometry arranged and disposed to fill the open section in the existing component, and securing the article within the open section of the existing component to form the component. Another method includes directly depositing a material, by an additive manufacturing technique, over a portion of the existing component.

Abstract: Methods for treating components formed from equiaxed material(s) or directionally solidified structures and treated components are disclosed. The method may include machining a portion of the component, and direct metal laser depositing a material on the machined portion of the component to form a deposited, directionally solidified structure integral with the component. The deposited, directionally solidified structure may include columnar dendrites. Additionally, the treated component may include a body including a machined portion. The machined portion of the body may be formed substantially from an equiaxed material or a preexisting directionally solidified structure. The body of the component may also include a deposited, directionally solidified structure formed directly on the machined portion of the body. The deposited, directionally solidified structure may be direct metal laser deposited on the machined portion of the body.

Abstract: A method for repairing a component is disclosed. The method includes removing a portion originally including a plurality of cooling holes, of the component to form a cavity, forming by additive manufacturing a replacement portion including a plurality of cooling holes, and varying a surface roughness and a diameter of at least one cooling hole of the plurality of cooling holes during the forming by additive manufacturing the replacement portion. The replacement portion replaces the portion of the component.

Abstract: A method for forming a secondary component from an original component having an original shape includes separating the original component into a parent component and a replaced portion, and forming a replacement coupon using an additive manufacturing system. The replacement coupon is shaped to substantially match the original shape of the replaced portion. The method further includes coupling the replacement coupon to the parent component to form the secondary component. The method also includes at least one of (i) removing the replacement coupon from a build plate of the additive manufacturing system prior to application of any heat treatment to the as-built replacement coupon, wherein the replacement coupon maintains a near-net original shape of the replaced portion after removal, and (ii) entering the secondary component into normal duty with no hot isostatic press treatment of the replacement coupon having been performed.

Abstract: Various embodiments include approaches for repairing a turbine component. In some cases, a method includes: removing a turbine component from a turbine rotor assembly; identifying at least one flaw in the turbine component; and direct metal laser melting (DMLM) or direct metal laser depositing (DMLD) a fill material to fill the at least one flaw in the turbine component, forming a repaired turbine component.

Abstract: A braze composition, brazing process, and brazed article are disclosed. The braze composition includes a MCrAlY alloy at a concentration, by weight, of between 50% and 70%, where M is selected from the group consisting of nickel, cobalt, iron, alloys thereof, and combinations thereof, and a nickel-based alloy at a concentration, by weight, of between 30% and 50%. The brazing process includes forming a braze paste, brazing the braze paste to a portion of a component, and shaping the braze paste to form a brazed article. The brazed article includes a component and a braze composition brazed to the component, the braze composition including a MCrAlY alloy at a concentration, by weight, of between 50% and 70%, where M is selected from the group consisting of nickel, cobalt, iron, alloys thereof, and combinations thereof, and a nickel-based alloy at a concentration, by weight, of between 30% and 50%.

Abstract: A process for forming an aluminide coating system on a substrate. The process includes preparing a slurry including, by weight, about 35 to about 65% of an aluminum donor powder, the aluminum donor material comprising at least 35% aluminum, about 1 to about 25% of a binder, and balance essentially carrier. The slurry is applied to the substrate. The substrate is a nickel or cobalt based superalloy being essentially free of aluminum. The slurry is heated to form an aluminide diffusion coating including an additive aluminide layer and an interdiffusion zone disposed between the substrate and the additive aluminide layer.

Abstract: A method of selectively applying an overlay coating to a coated article and a selectively treated coated article are provided. The method includes the steps of providing the coated article having a treatment region that includes a bond coat and a thermal barrier coating and selectively applying an overlay coating to the treatment region without stripping the treatment region from the coated article. The bond coat of the coated article which has been exposed to an operational temperature includes a first volume fraction of a ?-phase microstructure that is less than a second volume fraction of a ?-phase microstructure of a comparable bond coat of a comparable article which has not been exposed to the operational temperature. A coated article including an overlay coating selectively applied over a treatment region is also disclosed.

Abstract: A method for treating a coated article having a depleted layer following exposure of the coated article to an operational temperature is disclosed. The method includes applying an aluminizing composition to the article, forming an overlay aluminide coating on the article from the aluminizing composition, heat treating the overlay aluminide coating, and diffusing aluminum from the overlay aluminide coating into the depleted layer, transforming at least a portion of the depleted layer into a rejuvenated layer. The depleted layer includes a depleted concentration of aluminum relative to a corresponding layer of the coated article prior to the coated article being exposed to the operational temperature. The rejuvenated layer includes a rejuvenated concentration of aluminum which is elevated relative to the depleted concentration of aluminum. A treated article includes a substrate, a rejuvenated aluminide layer disposed on the substrate, and an overlay aluminide coating disposed on the rejuvenated aluminide layer.

Abstract: A system and method for thermal inspection of a component having at least one cooling hole is disclosed, that uses an evaporative membrane for direct evaporative cooling of an exhausted working fluid. A working fluid is supplied to at least one internal passage of a component that is configured to exhaust the working fluid from the internal passage sequentially through the cooling holes and the wetted evaporative membrane disposed in direct air-tight contact with the component. An imager captures a time series of images corresponding to a transient evaporative response of the exhausted working fluid to determine a plurality of temperature values for the exhausted working fluid after passage through the evaporative membrane. A processor circuit is configured to evaluate the transient evaporative response of the exhausted working fluid.

Abstract: A process of treating a component includes mechanically removing surface debris from a base coating of the component, identifying at least one surface feature in the base coating, and applying an overlay coating layer over the surface feature of the base coating without stripping off the base coating. A process of treating a gas turbine component includes mechanically removing surface debris from a base coating of the gas turbine component, identifying at least one surface feature in the base coating of corrosion pits, dents, spalls, and combinations thereof, and applying an overlay coating layer over the surface feature of the base coating without stripping off the base coating. A treated gas turbine component includes a gas turbine component substrate and a base coating on the gas turbine component substrate having at least one healed surface feature. The healed surface feature includes an overlay coating layer on the base coating.

Abstract: A braze composition, brazing process, and brazed article are disclosed. The braze composition includes a MCrAlY alloy at a concentration, by weight, of between 50% and 70%, where M is selected from the group consisting of nickel, cobalt, iron, alloys thereof, and combinations thereof, and a nickel-based alloy at a concentration, by weight, of between 30% and 50%. The brazing process includes forming a braze paste, brazing the braze paste to a portion of a component, and shaping the braze paste to form a brazed article. The brazed article includes a component and a braze composition brazed to the component, the braze composition including a MCrAlY alloy at a concentration, by weight, of between 50% and 70%, where M is selected from the group consisting of nickel, cobalt, iron, alloys thereof, and combinations thereof, and a nickel-based alloy at a concentration, by weight, of between 30% and 50%.

Abstract: A method of treatment includes laser-hardening a portion of a component and texturing a treated surface of the portion with a hydrophobic surface texture. In some embodiments, the method includes polishing the treated surface after laser-hardening the portion and prior to texturing the treated surface. A component includes a component body having a portion that is laser-hardened. The treated surface is hydrophobic with a hydrophobic surface texture. In some embodiments, the component is a turbine component. In some embodiments, the portion is a leading edge. A turbine system includes a turbine shaft and a turbine component attached to the turbine shaft. The turbine component includes a component body having a leading edge. The leading edge is laser-hardened and the treated surface of the leading edge is hydrophobic with a hydrophobic surface texture.

Abstract: A metallic structure having a graded microstructure is provided. The metallic structure comprises a graded region comprising a plurality of grains having a gradient in grain size varying as a function of position between a first median grain size at an outer region and a second median grain size at an inner region and a plurality of dispersoids dispersed within the microstructure. The first median grain size is different from the second median grain size. A method of forming a metallic structure having a graded microstructure is also provided. The method comprises: providing a metallic structure comprising at least one reactive species; diffusing at least one reactant at a controlled rate from an outer region of the metallic structure towards an inner region of the metallic structure to form a gradient in reactant activity; reacting the reactant with the reactive species to form a plurality of dispersoids; and heat treating the metallic structure to achieve grain growth so as to form a graded microstructure.

Abstract: A mechanical seal includes a pair of opposing seal faces, wherein at least one of the pair of seal faces comprises a multilayer coating disposed on a substrate, and wherein the multilayer coating comprises a periodic repetition of distinct layers. In another embodiment, the mechanical seal includes a pair of opposing seal faces, wherein at least one of the pair of seal faces comprises a multilayer coating disposed on a substrate, wherein the multilayer coating comprises a plurality of layers of a composite, and wherein no two adjacent layers of the composite comprise an identical ratio of composite constituents. A method includes disposing a multilayer coating on a substrate to form at least one of a pair of opposing seal faces of a mechanical seal.