Disclosed is a coated composite comprising a seal coat disposed on a composite material wherein the seal coat comprises protective particles and a matrix.

A supercharging device having a housing, at least one impeller, and at least one axial bearing having first and second bearing surfaces. The impeller here forms one of the bearing surfaces of the axial bearing.

Methods for depositing protective coatings on aerospace components are provided and include sequentially exposing the aerospace component to a chromium precursor and a reactant to form a chromium-containing layer on a surface of the aerospace component by an atomic layer deposition process. The chromium-containing layer contains metallic chromium, chromium oxide, chromium nitride, chromium carbide, chromium silicide, or any combination thereof.

During a material removal method, a component is received that includes a component body and a coating on the component body. The component body includes metallic first material. The coating includes second material that is different from the first material. A solution is received that includes nitric acid and hydrogen peroxide. At least a portion of the coating is subjected to the solution in order to remove at least some of the second material from the component.

Protected aerospace components are provided and contain a nanolaminate film stack disposed on a surface of an aerospace component, where the nanolaminate film stack comprises alternating layers of a chromium-containing layer and a second deposited layer. The chromium-containing layer can include metallic chromium, chromium oxide, chromium nitride, chromium carbide, chromium silicide, or any combination thereof.

A supercharging device having a housing, at least one impeller, and at least one axial bearing having first and second bearing surfaces. The impeller here forms one of the bearing surfaces of the axial bearing.

A method of manufacturing a CMC structure includes infiltrating a porous substrate with a composite material and performing a first densification on the infiltrated porous substrate, forming a first densified porous substrate, wherein the first densification includes techniques selected from the group of techniques comprising photonic curing, photonic sintering, pulsed thermal heating, or combinations thereof.

The invention relates to a guide vane assembly for a turbomachine, comprising a guide vane, which has a guide vane airfoil; and a guide vane holder. The guide vane is mounted in the guide vane holder such that the guide vane can be moved about an axis of rotation. For this purpose, the guide vane has at least one axle element, which is inserted into the guide vane holder in such a way that an outer lateral surface of the axle element faces an inner lateral surface of the guide vane holder. A protective coating is applied to at least parts of the guide vane airfoil. A protective coating is applied to at least one of the lateral surfaces. The invention also relates to a compressor module, a turbomachine, and a method for producing a guide vane assembly.

Methods for forming protective coatings on aerospace components are provided. In one or more embodiments, the method includes exposing an aerospace component to a first precursor and a first reactant to form a first deposited layer on a surface of the aerospace component by a first deposition process (e.g., CVD or ALD), and exposing the aerospace component to a second precursor and a second reactant to form a second deposited layer on the first deposited layer by a second deposition process. The first deposited layer and the second deposited layer have different compositions from each other. The method also includes repeating the first deposition process and the second deposition process to form a nanolaminate film stack having from 2 pairs to about 1,000 pairs of the first deposited layer and the second deposited layer consecutively deposited on each other.

Methods for forming protective coatings on aerospace components are provided. In one or more embodiments, the method includes exposing an aerospace component to a first precursor and a first reactant to form a first deposited layer on a surface of the aerospace component by a first deposition process (e.g., CVD or ALD), and exposing the aerospace component to a second precursor and a second reactant to form a second deposited layer on the first deposited layer by a second deposition process. The first deposited layer and the second deposited layer have different compositions from each other. The method also includes repeating the first deposition process and the second deposition process to form a nanolaminate film stack having from 2 pairs to about 1,000 pairs of the first deposited layer and the second deposited layer consecutively deposited on each other.