The thermal barrier coating includes reactive gadolinia in its microstructures and the embedded gadolinia effectively reacts with CMAS contaminant reducing the damage from CMAS. Moreover, a method to produce a CMAS resistant thermal barrier coating can include a post-treatment to the thermal barrier coating with the reactive gadolinia suspension in sol-gel state.

A thermal barrier coating includes a highly porous layer and a dense layer. The highly porous layer is formed on a heat-resistant base, is made of ceramic, has pores, has a layer thickness of equal to or larger than 0.3 mm and equal to or smaller than 1.0 mm, and has a pore ratio of equal to or higher than 1 vol % and equal to or lower than 30 vol %. The dense layer is formed on the highly porous layer, is made of ceramic, has a pore ratio of equal to or lower than 0.9 vol % that is equal to or lower than the pore ratio of the highly porous layer, and has a layer thickness of equal to or smaller than 0.05 mm.

The present invention relates to cathodes electrodes compositions suitable to provide a pumping mechanism which exhibits an extremely high pumping speed and capacity of noble gas suitable to be used in several vacuum devices as for example sputter ion vacuum pumping systems comprising them as active element.

A component for a gas turbine engine includes an airfoil section including a free end and an abrasive coating sprayed onto the free end, the abrasive coating including a polymer matrix and an abrasive filler, the abrasive filler between about 50%-75% by volume of the abrasive coating.

Provided is a special type of corrosion protection for ceramic thermal insulation layers which is produced by joining hollow aluminum oxide particles and an outer glass layer, which is produced; in particular, by thermal treatment.

A component for a gas turbine engine includes an airfoil section including a free end and an abrasive coating sprayed onto the free end, the abrasive coating including a polymer matrix and an abrasive filler, the abrasive filler between about 50%-75% by volume of the abrasive coating.

Disclosed is a method of reducing play in a vane arc segment. The vane arc segment includes an airfoil piece that defines first and second platforms and a hollow airfoil section that has an internal cavity and that extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a radial flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the radial flange, and a thermal insulation element is located adjacent the radial flange. The method includes performing a light scan of the radial flange to produce a digital three-dimensional model of the radial flange, and then machining the thermal insulation element in accordance with the digital three-dimensional model to provide a low-tolerance fit between the radial flange and the thermal insulation element that limits play between the airfoil piece and the thermal insulation element.

A gas turbine component for use in a gas turbine engine includes a substrate a ceramic-based thermal barrier coating (TBC), and a diffusion chromide bond coat between the base material and the TBC. A thermally grown oxide (TGO) layer can be formed on the bond coat prior to application of the TBC. The TBC and the TGO include a common metal oxide. The oxide can be sacrificially in use and soluble in a molten sulfate salt, make the coating system particularly suitable for use in a marine environment.

An article includes a substrate and a multi-layered ceramic barrier coating on a substrate. The coating includes, from the substrate outward, a first layer of a low-dopant ceramic material and a second layer high-dopant ceramic material. The first layer has a columnar microstructure and the second layer has a branched columnar microstructure.

A process for forming a thermal barrier coating system on a substrate is disclosed including preparing a slurry including a donor powder, an activator powder, and a binder. The donor powder includes a metallic aluminum alloy having a melting temperature higher than aluminum, and the binder includes at least one organic polymer gel. The process further includes applying the slurry to the substrate, heating the slurry to form an aluminide bond coating including an additive aluminide layer and an aluminide interdiffusion zone disposed between the substrate and the additive aluminide layer, and applying a thermal barrier coating to the aluminide bond coating. The thermal barrier coating may be a dense vertically-cracked thermal barrier coating, and the substrate may be a gas turbine component. Thermal barrier coating systems formed by the process are also disclosed.