A ceramic coating according to at least one embodiment of the present disclosure includes: a bond coat layer formed on a substrate; and a ceramic layer formed on the bond coat layer. The ceramic layer has a first region in contact with an interface between the ceramic layer and the bond coat layer and a second region father away from the interface than the first region from the interface. In a cross-section along a thickness direction of the ceramic layer, the number of crack intersection points at which two or more cracks intersect per unit area in the ceramic layer is larger in the first region than in the second region.

A method of assessing the quality of a bond coat for bonding a ceramic coating to a metallic substrate comprises determining a thresholded summit area for the bond coat.

An article includes a substrate, a ceramic barrier coating, and a layer of networked ceramic nanofibers. The ceramic barrier coating is disposed on the substrate and has a porous columnar microstructure. The layer of networked ceramic nanofibers is disposed on the ceramic barrier layer and seals the pores of the porous columnar microstructure.

Provided is a method for arranging a protective coating for a thermally stressed structure, having at least one layer of alpha-aluminium oxide or of element-modified alpha-aluminium oxide, and wherein the protective coating is applied by reactive cathodic arc vaporization. A protective coating produced by the method and a component having a protective coating is also provided.

A coating-substrate combination includes: a Ni-based superalloy substrate comprising, by weight percent: 2.0-5.1 Cr; 0.9-3.3 Mo; 3.9-9.8 W; 2.2-6.8 Ta; 5.4-6.5 Al; 1.8-12.8 Co; 2.8-5.8 Re; 2.8-7.2 Ru; and a coating comprising, exclusive of Pt group elements, by weight percent: Ni as a largest content; 5.8-9.3 Al; 4.4-25 Cr; 3.0-13.5 Co; up to 6.0 Ta, if any; up to 6.2 W, if any; up to 2.4 Mo, if any; 0.3-0.6 Hf; 0.1-0.4 Si; up to 0.6 Y, if any; up to 0.4 Zr, if any; up to 1.0 Re, if any.

Disclosed is a thermal barrier coating system for components of a turbomachine, especially for high temperature-stressed or hot gas-stressed components of a turbomachine, comprising a ceramic coating of fully or partially stabilized zirconium oxide, and an oxide cover coating which comprises aluminum and at least one element from the group lanthanum, magnesium, silicon, calcium and sodium. The aluminum oxide exists at least partially as free α-Al.sub.2O.sub.3. Also disclosed is a method for producing a corresponding thermal barrier coating system.

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.

The disclosure provides a eutectic ceramic thermal barrier material and a preparation method thereof, which relates to the field of composite materials. The present disclosure provides a eutectic ceramic thermal barrier material comprising a nickel-based superalloy substrate, an intermediate binding layer and a eutectic ceramic cladding layer stacked sequentially; the intermediate binding layer comprises a NiCoCrAlY binding layer; the eutectic ceramic cladding layer comprises an Al.sub.2O.sub.3/GdAlO.sub.3 binary eutectic ceramic coating or an Al.sub.2O.sub.3/GdAlO.sub.3/ZrO.sub.2 ternary eutectic ceramic coating. The eutectic ceramic thermal barrier material provided by the present disclosure has good high temperature resistance, good oxidation resistance and excellent mechanical properties.

A thermal barrier coating disposed on a substrate comprising a plurality of surface features formed on the substrate proximate an inner side of the substrate, each of the plurality of surface features comprising a metallic column having a top with rounded edges; a dense layer disposed in a valley located between each of the plurality of surface features, and the dense layer disposed on the top and covering the rounded edges; a thermally insulating topcoat disposed over the plurality of surface features.

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.