Embodiments of the present disclosure may comprise a protective coating, the protective coating comprising a bottom layer, comprising substantially a first material. and a top layer, comprising substantially diamond-like carbon. There is a blended layer between the bottom layer and the top layer, comprising first material and diamond-like carbon in varying concentrations.

Components for a gas turbine engine and method for producing the components are provided. The components may include a substrate and a thermal barrier coating (TBC) having at least a first layer secured to a surface of the substrate. The first layer is formed of a ceramic material with a first microstructure that includes a plurality of interconnected unit cells having struts that have a relative density of greater than 98 percent and a closed cell porosity of 10 percent or greater. The TBC is secured to the substrate subsequent to formation of the TBC.

A method for forming a chromium nitride coating over a substrate to provide a chromium nitride coated article, and the resulting chromium nitride coated article, each use a bilayer chromium nitride containing material layer. The bilayer chromium nitride containing material layer includes: (1) a first chromium nitride material layer having a first thickness, a first uniform chromium concentration and a first uniform nitrogen concentration located and formed closer to a substrate which provides the article; and (2) a second chromium nitride material layer having a second thickness, a second increasingly graded chromium concentration and a second decreasingly graded nitrogen concentration located and formed upon the first chromium nitride material layer. This particular bilayer chromium nitride containing material layer provides the article with superior reflectivity and crack resistance.

An erosion and corrosion resistant protective coating for turbomachinery application includes at least one ceramic or metal-ceramic coating segment deposited on surface of a conductive metal substrate subjected to a pre-deposition treatment by at least blasting to provide the surface with texture. The erosion and corrosion resistant coating has a plurality of dome-like structures with dome width between in range from about 0.01 m to about 30 m. The at least one coating segment is formed by condensation of ion bombardment from a metal-gaseous plasma flow, wherein, at least during deposition of first micron of the coating segment, deposition rate of metal ions is at least 3 m/hr and kinetic energy of deposited metal ions exceeds 5 eV.

There is disclosed method for manufacturing a cutting device comprising the steps of a) providing a base comprising a cutting edge, wherein the base is made of a base material comprising a first element, b) applying a first coating layer comprising a second element on the top surface of the base by a method selected from PVD and electroplating, c) heat treating the base, wherein the step c) is performed at a temperature and for a time period sufficient for the second element to diffuse partly into the base and for the first element to diffuse at least partly into the first coating layer, whereby a gradient of a compound is formed by a reaction of the first element and the second element. Advantages include that wear resistance properties and stay sharp properties are improved, which are particularly suitable for surfaces of cutting devices. Furthermore, the method is environmentally friendly.

A coating system for a turbine engine component is disclosed. The coating system includes a substrate, an optional bond coat, a synthetic oxide layer and a top coat. The synthetic oxide layer is formed by atomic layer deposition and includes two or more oxides.

An absorbing structure has a body provided on air vehicles. At least one transition metal alloy is located on the body that consists of two-dimensional inorganic compounds formed by bonding a plurality of carbon atoms and a plurality of nitrogen atoms. A plurality of layers contain the transition metal alloy. At least one barrier coating consists of the layers, which based on a conductivity of the layer, prevents and provides protection against plastic and/or elastic deformations that may occur on the body when an electromagnetic wave acts on the body.