Abstract: 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.

Abstract: 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 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.

Abstract: Embodiments of the present disclosure generally relate to protective coatings on turbine blades, turbine disks, and other aerospace components and methods for depositing the protective coatings. In one or more embodiments, a turbine blade includes a blade portion and a root coupled to the blade portion, where the root contains a protective coating disposed thereon. The protective coating is or contains one or more deposited crystalline film containing at least one of a metal oxide, a metal nitride, or a metal oxynitride and has a thickness of about 100 nm to about 10 ?m. In some examples, a turbine blade assembly includes a disk and a plurality of the turbine blades coupled to the disk. The protective coating is disposed on the root on the turbine blade and/or a receiving surface on the turbine disk.

Abstract: Embodiments described herein relate to a non-destructive measurement device measurement device and a non-destructive measurement method for determining coating thickness of a three-dimensional (3D) object. In one embodiment, at least one first 3D image of an uncoated surface of the object and at least one second 3D image of a coated surface of the object are collected and analyzed to the determine the coating thickness of the object.

Abstract: Embodiments of the present disclosure generally relate to protective coatings on substrates and methods for depositing the protective coatings. In one or more embodiments, a method of forming a protective coating on a substrate includes depositing a chromium oxide layer containing amorphous chromium oxide on a surface of the substrate during a first vapor deposition process and heating the substrate containing the chromium oxide layer comprising the amorphous chromium oxide to convert at least a portion of the amorphous chromium oxide to crystalline chromium oxide during a first annealing process. The method also includes depositing an aluminum oxide layer containing amorphous aluminum oxide on the chromium oxide layer during a second vapor deposition process and heating the substrate containing the aluminum oxide layer disposed on the chromium oxide layer to convert at least a portion of the amorphous aluminum oxide to crystalline aluminum oxide during a second annealing process.

Abstract: Embodiments described herein provide apparatus, software applications, and methods of a coating process, such as an Electron Beam Physical Vapor Deposition (EBPVD) of thermal barrier coatings (TBCs) on objects. The objects may include aerospace components, e.g., turbine vanes and blades, fabricated from nickel and cobalt-based super alloys. The apparatus, software applications, and methods described herein provide at least one of the ability to detect an endpoint of the coating process, i.e., determine when a thickness of a coating satisfies a target value, and the ability for closed-loop control of process parameters.

Abstract: Embodiments described herein provide apparatus, software applications, and methods of a coating process, such as an Electron Beam Physical Vapor Deposition (EBPVD) of thermal barrier coatings (TBCs) on objects. The objects may include aerospace components, e.g., turbine vanes and blades, fabricated from nickel and cobalt-based super alloys. The apparatus, software applications, and methods described herein provide at least one of the ability to detect an endpoint of the coating process, i.e., determine when a thickness of a coating satisfies a target value, and the ability for closed-loop control of process parameters.

Abstract: Protective coatings on an aerospace component are provided. An aerospace component includes a surface containing nickel, nickel superalloy, aluminum, chromium, iron, titanium, hafnium, alloys thereof, or any combination thereof, and a coating disposed on the surface, where the coating contains a nanolaminate film stack having two or more pairs of a first deposited layer and a second deposited layer. The first deposited layer contains chromium oxide, chromium nitride, aluminum oxide, aluminum nitride, or any combination thereof, the second deposited layer contains aluminum oxide, aluminum nitride, silicon oxide, silicon nitride, silicon carbide, yttrium oxide, yttrium nitride, yttrium silicon nitride, hafnium oxide, hafnium nitride, hafnium silicide, hafnium silicate, titanium oxide, titanium nitride, titanium silicide, titanium silicate, or any combination thereof, and the first deposited layer and the second deposited layer have different compositions from each other.

Abstract: Protective coatings on an aerospace component and methods for depositing the protective coatings are provided. A method for depositing a coating on an aerospace component 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 chemical vapor deposition (CVD) process or a first atomic layer deposition (ALD) process 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 ALD process, where the first deposited layer and the second deposited layer have different compositions from each other.

Abstract: Embodiments described herein relate to a non-destructive measurement device measurement device and a non-destructive measurement method for determining coating thickness of a three-dimensional (3D) object. In one embodiment, at least one first 3D image of an uncoated surface of the object and at least one second 3D image of a coated surface of the object are collected and analyzed to the determine the coating thickness of the object.

Abstract: A gas distribution assembly for applying a coating on an interior of a plurality of components includes a support with a plurality of component cavities formed within the support. Each component cavity corresponds to a respective component to fluidly couple with an interior of the respective component. A first gas source flow line is fluidly coupled with each of the component cavities to provide a first gas from a first gas source to each of the component cavities, and a second gas source flow line is fluidly coupled with each of the component cavities to provide a second gas from a second gas source to each of the component cavities.

Abstract: Embodiments of the present disclosure generally relate to protective coatings on an aerospace component and methods for depositing the protective coatings. In one or more embodiments, a method for depositing a protective coating on an aerospace component includes sequentially exposing the aerospace component to a chromium precursor and a reactant to form a chromium-containing layer on a surface 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.

Abstract: Embodiments of the present disclosure generally relate to protective coatings on an aerospace component and methods for depositing the protective coatings. In one or more embodiments, a method for depositing a coating on an aerospace component 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 chemical vapor deposition (CVD) process or a first atomic layer deposition (ALD) process 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 ALD process, where the first deposited layer and the second deposited layer have different compositions from each other.

Abstract: The present invention relates to purified transparent carbon nanotube (CNT) conductive layers or coatings that comprise at least one additional material to form a composite. Adding a material to the CNT layer or coating improves conductivity, transparency, and/or the performance of a device comprising a transparent conductive CNT layers or coating This composite may be used in photovoltaic devices, OLEDs, LCD displays, or touch screens.

Abstract: This invention are directed to methods and compositions preferably comprising non-silicate metal oxides as a treatment for transparent electrically conductive carbon nanotube coatings that prevents resistance changes during exposure to environmental conditions; both chemical effects (for example, water, heat, light, or other compounds) and physical effects (for example, abrasion, scratch, adhesion). The protective properties instilled by these coatings occur preferably through the careful selection of the appropriate metal oxide depending on the application.

Abstract: This invention is directed to compositions and methods of incorporating metal particles into carbon nanotube films, sheets, and networks. Metal salts that are soluble in water, alcohol, polar organic solvents, and mixtures thereof are used to deposit metal particles onto carbon nanotube films, sheets, and networks. Metal salts increase conductance of nanotube films by spontaneously depositing gold on the nanotube. The concentration and time of exposure to metal salt solution allows the tuning of conductivity and transparency for a transparent carbon nanotube network. Metal salts added to nanotube ink add functional properties of the metal to nanotube conductors.