Abstract: A method of reducing depletion of elements from an airfoil includes disposing a bond coating on the airfoil, where the airfoil comprises cooling channels. The airfoil includes a material that has an initial composition. A cooling hole is machined in the airfoil to contact the cooling channels such that a fluid travelling in the cooling channel may be discharged via the cooling hole. The machining of the cooling hole results in a formation of a depleted region around the cooling hole. The depleted region is depleted of a portion of the initial composition of the airfoil. A top coat is disposed on the bond coat. The airfoil is subjected to a heat treatment at a temperature effective to promote diffusion of elements from a non-depleted region to the depleted region around the cooling hole.

Abstract: A method of repairing, or manufacturing, a tip for an airfoil can comprise: removing a portion of the airfoil that reduces a radial height of the airfoil and defines a first mating surface of the airfoil; forming a blade tip body for the airfoil, the blade tip body defining a second mating surface; and joining the first mating surface to the second mating surface via a Field Assisted Sintering Technology (“FAST”) process.

Abstract: A method can comprise forming a component comprising a first mating surface; coupling the component to an airfoil having a second mating surface and a Field Assisted Sintering Technology (“FAST”) system; heating, via the FAST system, the airfoil and the component; and applying, via the FAST system, a mechanical pressure between the first mating surface and the second mating surface to join the airfoil to the component and form a blade, the component at least partially defining a leading edge of the blade in response to joining the airfoil to the component

Abstract: A method of repairing a tip for an airfoil is disclosed herein. In various embodiments, the method comprises: removing a portion of the airfoil that reduces a radial height of the airfoil and at least partially removes a defect of the airfoil; removing a remainder of the defect; joining, via gas tungsten arc welding, a filler material to the airfoil to repair the defect; and joining a first mating surface of the airfoil to a second mating surface of a blade tip body via a solid-state joining process.

Abstract: A method for applying an abrasive comprises: applying, to a substrate, the integral combination of: a self-braze material; and an abrasive embedded in the self-braze material; and securing the combination to the substrate.

Abstract: A method of coating includes applying a metallic coating slurry without a filler to a component; draining the metallic coating slurry; drying the metallic coating slurry to drive off the organic binder; and heat treating the component.

Abstract: A process for applying a chromium layer on a substrate, specifically a turbine engine airfoil, by contacting at least a portion of the substrate with a gaseous chromium wherein the gaseous chromium is generated from a substantially nitrogen free source.

Abstract: A method for applying an abrasive comprises: applying, to a substrate, the integral combination of: a self-braze material; and an abrasive embedded in the self-braze material; and securing the combination to the substrate.

Abstract: A method for applying an abrasive comprises: applying, to a substrate, the integral combination of: a self-braze material; and an abrasive embedded in the self-braze material; and securing the combination to the substrate.

Abstract: A process for applying a chromium layer on a substrate, specifically a turbine engine airfoil, by contacting at least a portion of the substrate with a gaseous chromium wherein the gaseous chromium is generated from a substantially nitrogen free source.

Abstract: A method for applying an abrasive comprises: applying, to a substrate, the integral combination of: a self-braze material; and an abrasive embedded in the self-braze material; and securing the combination to the substrate.

Abstract: The present disclosure relates generally to method for preparing metallographic samples including the steps of placing a specimen into a mold, inserting an epoxy into the mold, and exposing the mold to an ultraviolet light for a duration of time to create a mounting sample. The mold includes a peripheral wall and a bottom defining a cavity therein. The mold is formed from a material that allows ultraviolet light to penetrate the peripheral wall and bottom into the cavity. The mold includes a material operative to allow an ultraviolet light to penetrate the peripheral wall and the bottom surface into the cavity.

Abstract: An abrasive sheath for application to a component surface is disclosed. The abrasive sheath may comprise a metallic layer and an abrasive layer plated on a surface of the metallic layer. The abrasive layer may include a metal matrix and abrasive particles protruding from the matrix. An exposed surface of the metallic layer of the abrasive sheath may be joinable to the component surface by a heat treatment.

Abstract: A method for applying an abrasive comprises: applying, to a substrate, the integral combination of: a self-braze material; and an abrasive embedded in the self-braze material; and securing the combination to the substrate.

Abstract: A method for repairing a blade wherein the blade comprises a metallic substrate shaped to define an airfoil having a tip. A coating is on the tip. The method comprises: machining to at least partially remove the coating; plating a nickel-based base layer; and plating an abrasive layer comprising a nickel-based matrix and an abrasive.

Abstract: A process for applying a chromium layer on a substrate, specifically a turbine engine airfoil, by contacting at least a portion of the substrate with a gaseous chromium wherein the gaseous chromium is generated from a substantially nitrogen free source.

Abstract: A method for applying an abrasive comprises: applying, to a substrate, the integral combination of a self-braze material, an abrasive, a matrix in which the abrasive is at least partially embedded, and an intermediate layer between the self-braze material and the matrix; and heating to cause the self-braze material to braze to the substrate.

Abstract: A method for applying an abrasive comprises: applying, to a substrate, the integral combination of: a self-braze material; an abrasive; and a matrix in which the abrasive is at least partially embedded; and heating to cause the self-braze material to braze to the substrate. The heating leaves at least a portion of the self-braze material with a composition comprising, in weight percent: cobalt 2.5-13.5; chromium 12-27; aluminum 5-7; yttrium 0.0-1.0; hafnium 0.0-1.0; silicon 1.0-3.0; tantalum 0.0-4.5; tungsten 0.0-6.5; rhenium 0.0-2.0; molybdenum 0.1-1.0; and the balance nickel.

Abstract: The present disclosure relates generally to strip process for removing a coating from a substrate comprising the steps of: providing a base alloy and a MCrAlY coating deposited over the base alloy substrate; and removing the MCrAlY coating by bringing the MCrAlY coating in contact with an acid solution comprising nitric acid, phosphoric acid and ammonium bifluoride in an aqueous solution, and maintaining the acid solution contact for sufficient time and at sufficient temperature to permit the coating to be stripped from the base alloy substrate.

Abstract: Methods are provided for coating a component. In one such method, the component is disposed with metal alloy gravel comprising aluminum. An aluminide coating is then formed on the component, where the aluminum from the metal alloy gravel diffuses into the component to form the aluminide coating.