A process for coating a gas turbine engine disk comprises placing the disk having an outer surface into a chamber, the chamber configured to perform atomic layer deposition; injecting a first reactant into the chamber; forming a first monolayer gas thin film on the outer surface; removing the first reactant from the chamber; injecting a second reactant into the chamber; reacting second reactant with the first monolayer gas thin film; removing the second reactant from the chamber; and forming a protective barrier coating on the outer surface.

A method of assembling a part is provided and includes forming a first section of the part, defining, in the first section, passages with dimensions as small as 0.005 inches (0.127 mm), forming a second section of the part, metallurgically bonding the first and second sections whereby the passages are delimited by the first and second sections and executing the metallurgically bonding without modifying a condition of the passages.

Methods for repairing the conventional physical barrier coating barrier on a component having a damaged portion. Applying a coating on the outer surface of the damaged portion of the component. The coating containing a reactive oxide. Initiating a reaction between the coating and the molten sulfates within the outer surface of the component. The reaction catalytically decomposes molten sulfates at the outer surface of the damaged portion of the component.

Protected aerospace components are provided and contain a nanolaminate film stack disposed on a surface of an aerospace component, where the nanolaminate film stack comprises alternating layers of a chromium-containing layer and a second deposited layer. The chromium-containing layer can include metallic chromium, chromium oxide, chromium nitride, chromium carbide, chromium silicide, or any combination thereof.

A composite article comprises a substrate, the substrate comprising a silicon containing material and an additive comprising boron nitride nanotubes.

A coated article includes a substrate and an MCrAlY coating supported on the substrate. The M includes at least one of nickel, cobalt, and iron, Cr is chromium, Al is aluminum, and Y is yttrium. The composition of the MCrAlY coating varies in an amount of at least one of Cr, Al, and Y by location on the substrate with respect to localized property requirements. In one example, the coated article is an article of a gas turbine engine.

The present disclosure provides a wear liner for a stator vane that has a first hook and a second hook that are connected by a base, providing in a generally S-shaped channel. The wear liner includes an outer surface that is adapted to lie against a first component and an inner surface that is adapted to lie against a second component. The first hook of the wear liner includes a first engaging end that is adapted to engage a first component, while the second hook is adapted to engage the second component. The first component may comprise a vane foot and the second component may comprise a slot for receiving and securing the vane foot.

Embodiments of the present disclosure generally relate to methods for cleaning aerospace components having oxidation, corrosion, contaminants, and/or other degradations. In one or more embodiments, a cleaning method includes positioning the aerospace component into a processing region of a processing chamber, introducing hydrogen gas into the processing region, maintaining the processing region at a pressure of about 100 mTorr to about 5,000 mTorr, and heating the aerospace component at a temperature of about 500° C. to about 1,200° C. for about 0.5 hours to about 24 hours to produce a cleaned surface on the aerospace component. In other embodiments, a cleaning method includes exposing the aerospace component to ozone while maintaining the aerospace component at a temperature of about 15° C. to about 500° C. for 0.25 hours to about 24 hours to produce a cleaned surface on the aerospace component.

The present invention relates to a coating material for the production of an anti-corrosion and/or adhesion promoter layer, which material comprises metal powder and a phosphate-ion-containing solution as the binder, the metal powder being at least partially coated with Si or Si alloys or the binder consisting of phosphoric acid and metal phosphates and being substantially free of chromates. The invention further relates to a method for producing an anti-corrosion and/or adhesion promoter layer, comprising the following steps: Providing a coating material, such as indicated above, applying the coating material to a component surface on which the anti-corrosion and/or adhesion promoter layer is to be created, and drying and/or hardening by way of a heat treatment at a first temperature.

A coating process comprising applying to a surface a coating composition consisting essentially of an alkali metal silicate and an aqueous liquid phase having dispersed therein solid aluminum particles to form on the surface a wet coating; and drying said wet coating: under conditions which convert said wet coating to an electrically conductive, corrosion-resistant, solid coating; or under conditions which form a solid coating which is not electrically conductive (non-conductive) and thereafter treating said non-conductive coating under conditions which convert said non-conductive coating to an electrically conductive, corrosion-resistant coating.