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.

An abrasive coating system for a substrate of an airfoil in a turbine engine high pressure compressor, comprising a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, the matrix material consisting of unalloyed chromium and unalloyed aluminum distributed throughout the matrix material, wherein the grit particles extend above the matrix material relative to the top surface; and a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material.

A composite substrate includes, in this order: a ceramic plate; a metal layer containing at least one selected from the group consisting of aluminum and an aluminum alloy; and a thermal sprayed layer containing at least one selected from the group consisting of copper and a copper alloy, and an intermetallic compound containing copper and aluminum as constituent elements is scattered between the metal layer and the thermal sprayed layer.

An abrasive coating system for a substrate of an airfoil in a turbine engine high pressure compressor, comprising a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, the matrix material consisting of unalloyed chromium and unalloyed aluminum distributed throughout the matrix material, wherein the grit particles extend above the matrix material relative to the top surface; and a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material.

A turbine engine has: a first member (22) having a surface bearing an abradable coating, the abradable coating (36) being at least 90% by weight ceramic; and a second member (24) having a surface bearing an abrasive coating. The abrasive coating (56) has a metallic matrix (64) and a ceramic oxide abrasive (66) held by the metallic matrix, the first member and second member mounted for relative rotation with the abrasive coating facing or contacting the abradable coating. At least 50% by weight of the ceramic abrasive has a melting point at least 400K higher than a melting point of at least 20% by weight of the ceramic of the abradable coating.

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 spray coating film has a first spray coating film formed on a surface of an aluminum substrate and a second spray coating film formed on a surface of the first spray coating film. In the first spray coating film, an inorganic material with a layered crystalline structure is dispersed in a Ni-based alloy material, and an area ratio of the inorganic material is in a range from 40% to 80% relative to the sectional area of the first spray coating film. The second spray coating film is a porous film composed of ZrO.sub.2—SiO.sub.2 based ceramic containing 30% to 50% by mass of SiO.sub.2, and the second spray coating film has an area ratio of pores of 30% to 80% relative to the sectional area of the second spray coating film.

This invention relates to a method, system and apparatus for cladding a surface of an articles subject to corrosive, erosive or abrasive wear, such as impact or grinding tools. The method includes providing a supply of stock material and feeding the stock material towards a portion of the surface of the article via a dedicated feed source. A dedicated heat source heats the fed stock material and the portion of the surface of the article such that the heated stock material and the portion of the surface at least partially melt. Upon removal of the heat, the molten feedstock and the surface portion form a bonded coating layer on at least a portion of the surface of the article, thereby protecting that part of the assembly against wear.

A solar selective coating includes a substrate, a cermet layer having nanoparticles therein deposited on the substrate, and an anti-reflection layer deposited on the cermet layer. The cermet layer and the anti-reflection layer may each be formed of intermediate layers. A method for constructing a solar-selective coating is disclosed and includes preparing a substrate, depositing a cermet layer on the substrate, and depositing an anti-reflection layer on the cermet layer.

A turbine part, such as a turbine blade or a distributor fin, for example, including a substrate made of superalloy based on monocrystalline nickel, including rhenium and/or ruthenium, and having a γ′-NisAI phase that is predominant by volume and a γ-Ni phase, the part also including a sublayer made of metal superalloy based on nickel covering the substrate, wherein the sublayer has a γ′-NisAI phase that is predominant by volume and wherein the sublayer has an average atomic fraction of aluminium of between 0.15 and 0.25, of chromium of between 0.03 and 0.08, of platinum of between 0.01 and 0.05, of hafnium of less than 0.01 and of silicon of less than 0.01. A process for manufacturing a turbine part including a step of vacuum deposition of a sublayer made of a superalloy based on nickel having predominantly by volume a γ′-NisAI phase, on a substrate made of superalloy based on nickel including rhenium and/or ruthenium.