A bushing for a stator vane assembly of a gas turbine engine has a tubular member that is coaxial about a longitudinal axis and that extends a length between a first axial end and a second axial end. The tubular member has an outside circumferential surface thereon and an inside circumferential surface therein and is manufactured from a cobalt based alloy, a nickel based alloy, a graphite material, a cermet material or an alloy matrix comprising titanium, aluminum, niobium, manganese, boron, and carbon and a solid lubricant being dispersed in the alloy matrix. A portion of the inside circumferential surface and/or a portion of the outside circumferential surface has a wear resistant material thereon.

A coated substrate comprising a metal or metal alloy such as a high speed steel, TiAl based alloy or Ni based alloy or an electrically conductive ceramic material, wherein the coating comprises a hard material protective coating comprising alternating layers of different compositions, wherein a first composition of the alternating layers comprises silicon, Si, and/or a second composition of the alternating layers comprises boron, B.

A sensor assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a substrate layer formed on a localized surface of a rotatable gas turbine engine component, and at least one pair of transducers deposited on the substrate layer.

A layer system having a metallic substrate, in particular made of a >=9% by weight chromium steel, in particular with roughness of the substrate <=2 m and optionally an intervening chromium layer directly on the substrate, in particular made of Cr/CrN, an underlayer or middle layer of AlCr, and an outer layer, in particular outermost layer, of AlCrO, where the AlCr and AlCrO layers in particular are PVD coatings wherein a shark skin effect is achieved with a simple geometric arrangement, and can be used particularly for compressor blades.

An objective of the invention to provide an alloy article that exhibits even better mechanical properties and/or even higher corrosion resistance than conventional high entropy articles without sacrificing the attractive properties thereof, a product formed of the alloy article, and a fluid machine having the product. An alloy article according to the invention has a predetermined chemical composition comprising: Co, Cr, Fe, Ni and Ti, each within a range of 5 atomic % or more and 35 atomic % or less; Mo within a range of more than 0 atomic % and less than 8 atomic %; an element with a larger atomic radius than the atomic radiuses of Co, Cr, Fe and Ni within a range of more than 0 atomic % and 4 atomic % or less; and a balance of inevitable impurities.

Provided is a heat-resistant titanium (Ti) alloy member having excellent mechanical characteristics and oxidation resistance at high temperatures and having less mechanical anisotropy, a method for producing such a titanium alloy member, and a product including such an alloy member. A titanium-based alloy member includes titanium (Ti) as a major element and at least 0.5 to 2.0 mass % of boron (B) and has a dispersion of fiber-like TiB particles precipitated in a polycrystal matrix phase, the TiB particles each having a long axis of 1 to 10 m and a short axis of 0.01 to 0.5 m or less and having an aspect ratio of 2 to 1000, the TiB particles precipitating in a crystallographically random direction in each of crystal grains of the matrix phase.

An intermetallic matrix composite has an intermetallic matrix and a ceramic reinforcement. The intermetallic matrix comprises, in atomic percent: 28.02.0 Nb; 27.02.0 Mo; 27.02.0 Cr; 9.0 2.0 Si; 9.0 2.0 Al; and no more than 10.0 other alloying elements and impurities, if any.

A method (400) for coating a tip (106) of an aerofoil (100) is provided. The method (400) includes depositing a layer of nickel-based gamma/gamma prime chemistry (112) on the tip (106) of the aerofoil (100). The method (400) further includes depositing plurality of abrasive particles (114) on the layer of nickel-based gamma/gamma prime chemistry (112) to form a coating matrix (116). The method (400) further includes heating the tip (106) of the aerofoil (100) at a predetermined temperature in order to perform heat treatment of the coating matrix (116) and increase the strength of the coating (110) on the tip (106) of the aerofoil (100).

A coated substrate comprising a metal or metal alloy such as a high speed steel, TiAl based alloy or Ni based alloy or an electrically conductive ceramic material, wherein the coating comprises a hard material protective coating comprising alternating layers of different compositions, wherein a first composition of the alternating layers comprises silicon, Si, and/or a second composition of the alternating layers comprises boron, B.

A sensor assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a substrate layer formed on a localized surface of a rotatable gas turbine engine component, and at least one pair of transducers deposited on the substrate layer.