A coating system for a surface of a superalloy component is provided. The coating system includes a MCrAlY coating on the surface of the superalloy component, where M is Ni, Fe, Co, or a combination thereof. The MCrAlY coating generally has a higher chromium content than the superalloy component. The MCrAlY coating also includes a platinum-group metal aluminide diffusion layer. The MCrAlY coating includes Re, Ta, or a mixture thereof. Methods are also provided for forming a coating system on a surface of a superalloy component.

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.

A thermally dissipative article and a method of forming a thermally dissipative article are disclosed. The thermally dissipative article includes a component, a porous material formed in a layer on the component. The method of forming a thermally dissipative article includes providing a metal powder mixture and a soluble particulate mixture which forms a porous coating upon sintering and immersion in a solvent to remove the soluble particulate.

A process for producing a thermal barrier coating having an excellent thermal barrier effect and superior durability to thermal cycling. Also, a turbine member having a thermal barrier coating that has been formed using the production process, and a gas turbine. The process for producing a thermal barrier coating includes: forming a metal bonding layer (12) on a heat-resistant alloy substrate (11), and forming a ceramic layer (13) on the metal bonding layer (12) by thermal spraying of thermal spray particles having a particle size distribution in which the 10% cumulative particle size is not less than 30 μm and not more than 100 μm.

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.

An article has a metallic substrate having a plurality of recesses. A first coating is at least at the recesses and has: a splatted layer; and a columnar layer atop the splatted layer. A second coating is away from the recesses and has: a columnar layer atop the substrate without an intervening splatted layer.

By continuously long engravings, the spallation behavior of the thermal barrier coating is reduced and the lifetime of the TBC is prolonged.

A component of a gas turbine engine comprises a substrate, a corrosion resistant top layer, and an intermediate corrodible layer disposed between the corrosion resistant top layer and the substrate. When corroding, the intermediate layer has a color contrasting with a color of the top layer. A method of detecting a crack when it penetrated the top layer in a component of a gas turbine engine having a corrosion resistant top layer and an intermediate corrodible layer comprises, in sequence, observing that at least one area of the component has a color contrasting with that of the top layer; determining that the color of the at least one area is a result of corrosion of the intermediate corrodible layer; and determining that the top layer has a crack as a result of determining corrosion of the intermediate layer. A method of facilitating crack detection in a component is also presented.

An article including a substrate and a plurality of coatings disposed on the substrate is presented. The plurality of coatings includes a thermal barrier coating disposed on the substrate; and a protective coating including a calcium-magnesium-aluminum-silicon-oxide (CMAS)-reactive material disposed on the thermal barrier coating. The CMAS-reactive material has an orthorhombic weberite crystal structure. The CMAS-reactive material is present in the plurality of coatings in an effective amount to react with a CMAS composition at an operating temperature of the thermal barrier coating, thereby forming a reaction product having one or both of melting temperature and viscosity greater than that of the CMAS composition. A method of making the article and a related turbine engine component are also presented.

A system and method for performing laser induced breakdown spectroscopy during laser ablation of a coating, such as a TBC coating, deposited on a surface of a component, particularly to enable obtained spectrometry signals of the ablated coating to be used to monitor and control the laser ablation removal process in real-time. The system includes a laser energy source and a scan head interconnected with the laser energy source to receive a laser beam therefrom and then direct the laser beam onto the surface of the coated component. Collection optics collect radiation emitted from a laser-induced plasma generated by the laser beam at the surface of the coated component. The system is further equipped to spectrally analyze the radiation and generate a feedback signal for control and optimization of one or more operational parameters of the laser energy source in real-time.