A coated component, along with methods of its formation and use, is provided. The coated component includes a ceramic matrix composite (CMC) substrate comprising silicon carbide and having a mullite bondcoat on its surface. The mullite bondcoat includes an oxygen getter phase contained within a mullite phase. For example, the mullite bondcoat may include 60% to 98% by volume of the mullite phase. An environmental barrier coating is on the mullite bondcoat.

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 includes applying a material coating on a surface of a machine component using a thermal spray, wherein the material coating is formed from a combination of a hardfacing material and aluminum-containing particles. The method also includes thermally treating the material coating to generate an oxide layer comprising aluminum from the aluminum-containing particles, wherein the oxide layer is configured to reduce oxidation of the hardfacing material.

A method for manufacturing a planet gear or a sun gear of a gearbox of a wind turbine includes forming a base of the planet gear via at least one of casting or forging. The base of the planet gear includes an inner circumferential surface and an outer circumferential surface. Therefore, at least one of the inner circumferential surface or the outer circumferential surface of the planet gear includes a plurality of net or near-net gear teeth. The method also includes applying a coating material to at least a portion of the base of the gear and at least a portion of the plurality of gear teeth of the gear via an additive manufacturing process so as to increase a hardness of the portions of the base and the plurality of gear teeth that includes the coating material.

An alpha-alumina coated turbocharger turbine wheel includes a hub portion, a plurality of blades disposed about the hub portion, each blade of the plurality of blades having a leading edge and a trailing edge, a centerline passing axially through the hub portion, and a back-side wall defined radially between the leading edge of each blade of the plurality of blades and the centerline. The turbocharger turbine wheel is made of a metal alloy and a surface coating layer of alpha-alumina. The surface coating layer of alpha-alumina may be disposed only on the hub portion, the plurality of blades, and a radially-outer portion of the back-side wall. The radially-outer portion is defined between a radial distance from the centerline and the leading edge of each blade of the plurality of blades. Alternatively, the surface coating layer of alpha-alumina may be disposed on the hub portion, the plurality of blades, and an entirety of the back-side wall.

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 turbine system including a sealing component is presented. The sealing component includes a ceramic material. The ceramic material includes grains having an average grain size of less than 10 microns. A turbine shroud assembly including the sealing component is also presented.

A coating process for applying a bifurcated coating to an article is disclosed including applying an aluminizing slurry to a first portion of the article, applying a chromizing slurry to a second portion of the article, and simultaneously heat treating the article, the aluminizing slurry, and the chromizing slurry. Heat treating the aluminizing slurry forms an aluminide coating on the first portion of the article and an aluminide diffusion zone between the article and the aluminide coating. Heat treating the chromizing slurry forms a chromide coating on the second portion of the article and a chromide diffusion zone between the article and the chromide coating. The first portion and the second portion are both maintained in an unmasked state while applying the aluminizing slurry and the chromizing slurry and during the heat treating.

High temperature stable thermal barrier coatings useful for substrates that form component parts of engines such as a component from a gas turbine engine exposed to high temperatures are provided. The thermal barrier coatings include a multiphase composite and/or a multilayer coating comprised of two or more phases with at least one phase providing a low thermal conductivity and at least one phase providing mechanical and erosion durability. Such low thermal conductivity phase can include a rare earth zirconate and such mechanical durability phase can include a rare earth a rare earth aluminate. The different phases are thermochemically compatible even at high temperatures above about 1200° C.

A slidable component including a wear-resistant coating includes a slidable component, and a wear-resistant coating provided on a slide surface of the slidable component. The wear-resistant coating includes metal particles deposited on the side surface of the slidable component, and containing Ni, Co and Cr, and a first oxide layer covering surfaces of the metal particles, containing an Al oxide as its main component, and containing a Y oxide.