Abstract: Embodiments of the present disclosure generally relate to optically densified nanoimprint films and processes for making these optically densified nanoimprint films, as well as optical devices containing the optically densified nanoimprint films. In one or more embodiments, a method of forming a nanoimprint film includes positioning a substrate containing a porous nanoimprint film within a processing chamber, where the porous nanoimprint film contains nanoparticles and voids between the nanoparticles, and the porous nanoimprint film has a refractive index of less than 2. The method also includes depositing a metal oxide on the porous nanoimprint film and within at least a portion of the voids to produce an optically densified nanoimprint film during an atomic layer deposition (ALD) process.

Abstract: Using the systems and methods discussed herein, CMAS corrosion is inhibited via CMAS interception in an engine environment and/or is prevented or reduced by the formation of a metal oxide protective coating on a hot engine section component. The CMAS interception can occur while the engine is in operation in flight or in a testing or quality control environment. The metal oxide protective coating can be applied over other coatings, including Gd-zirconates (GZO) or yttria-stabilized zirconia (YSZ). The metal oxide protective coating is applied at original equipment manufacturers (OEM) and can also be applied in-situ using a gas injection system during engine use in-flight or during maintenance or quality testing. The metal oxide protective coating contains a rare earth element, aluminum, zirconium, chromium, or combinations thereof.

Abstract: Using the systems and methods discussed herein, CMAS corrosion is inhibited via CMAS interception in an engine environment and/or is prevented or reduced by the formation of a metal oxide protective coating on a hot engine section component. The CMAS interception can occur while the engine is in operation in flight or in a testing or quality control environment. The metal oxide protective coating can be applied over other coatings, including Gd-zirconates (GZO) or yttria-stabilized zirconia (YSZ). The metal oxide protective coating is applied at original equipment manufacturers (OEM) and can also be applied in-situ using a gas injection system during engine use in-flight or during maintenance or quality testing. The metal oxide protective coating contains a rare earth element, aluminum, zirconium, chromium, or combinations thereof and can have a thickness from 1 nm to 3,000 nm.

Abstract: Using the systems and methods discussed herein, CMAS corrosion is inhibited via CMAS interception in an engine environment and/or is prevented or reduced by the formation of a metal oxide protective coating on a hot engine section component. The CMAS interception can occur while the engine is in operation in flight or in a testing or quality control environment. The metal oxide protective coating can be applied over other coatings, including Gd-zirconates (GZO) or yttria-stabilized zirconia (YSZ). The metal oxide protective coating is applied at original equipment manufacturers (OEM) and can also be applied in-situ using a gas injection system during engine use in-flight or during maintenance or quality testing. The metal oxide protective coating contains a rare earth element, aluminum, zirconium, chromium, or combinations thereof.

Abstract: Using the systems and methods discussed herein, CMAS corrosion is inhibited via CMAS interception in an engine environment and/or is prevented or reduced by the formation of a metal oxide protective coating on a hot engine section component. The CMAS interception can occur while the engine is in operation in flight or in a testing or quality control environment. The metal oxide protective coating can be applied over other coatings, including Gd-zirconates (GZO) or yttria-stabilized zirconia (YSZ). The metal oxide protective coating is applied at original equipment manufacturers (OEM) and can also be applied in-situ using a gas injection system during engine use in-flight or during maintenance or quality testing. The metal oxide protective coating contains a rare earth element, aluminum, zirconium, chromium, or combinations thereof, and is from 1 nm to 3 microns in thickness.

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 of the present disclosure generally relate to protective coatings on aerospace components and methods for depositing the protective coatings. In one or more embodiments, a method for producing a protective coating on an aerospace component includes depositing a metal oxide template layer on the aerospace component containing nickel and aluminum (e.g., nickel-aluminum superalloy) and heating the aerospace component containing the metal oxide template layer during a thermal process and/or an oxidation process. The thermal process and/or oxidation process includes diffusing aluminum contained within the aerospace component towards a surface of the aerospace component containing the metal oxide template layer, oxidizing the diffused aluminum to produce an aluminum oxide layer disposed between the aerospace component and the metal oxide template layer, and removing at least a portion of the metal oxide template layer while leaving the aluminum oxide layer.

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 depositing one or more layers on a surface of the aerospace component using an atomic layer deposition or chemical vapor deposition process, and performing a partial oxidation and annealing process to convert the one or more layers to a coalesced layer having a preferred phase crystalline assembly. During oxidation cycles, an aluminum depleted region is formed at the surface of the aerospace component, and an aluminum oxide region is formed between the aluminum depleted region and the coalesced layer. The coalesced layer forms a protective coating, which decreases the rate of aluminum depletion from the aerospace component and the rate of new aluminum oxide scale formation.

Abstract: The present disclosure relates to a method of depositing a polymer layer, including: providing a substrate, having a sensor structure disposed on the substrate, to a substrate support within a hot wire chemical vapor deposition (HWCVD) chamber; providing a process gas comprising an initiator gas and a monomer gas and a carrier gas to the HWCVD chamber; heating a plurality of filaments disposed in the HWCVD chamber to a first temperature sufficient to activate the initiator gas without decomposing the monomer gas; and exposing the substrate to initiator radicals from the activated initiator gas and to the monomer gas to deposit a polymer layer atop the sensor structure.

Abstract: Embodiments of the present disclosure generally relate to nanocomposite pellicles for extreme ultraviolet lithography systems. A pellicle comprises a plurality of carbon nanotubes arranged in a planar sheet formed from a plurality of metal catalyst droplets. The plurality of carbon nanotubes are coated in a first conformal layer of boron nitride. The pellicle may comprise a plurality of boron nitride nanotubes formed simultaneously as the first conformal layer of boron nitride. The pellicle may comprise a carbon nanotube coating disposed on the first conformal layer of boron nitride and a second conformal layer of boron nitride or boron nitride nanotubes disposed on the carbon nanotube coating. The pellicle is UV transparent and is non-reactive in hydrogen radical environments.

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: Using the systems and methods discussed herein, CMAS corrosion is inhibited via CMAS interception in an engine environment and/or is prevented or reduced by the formation of a metal oxide protective coating on a hot engine section component. The CMAS interception can occur while the engine is in operation in flight or in a testing or quality control environment. The metal oxide protective coating can be applied over other coatings, including Gd-zirconates (GZO) or yttria-stabilized zirconia (YSZ). The metal oxide protective coating is applied at original equipment manufacturers (OEM) and can also be applied in-situ using a gas injection system during engine use in-flight or during maintenance or quality testing. The metal oxide protective coating contains a rare earth element, aluminum, zirconium, chromium, or combinations thereof, and is from 1 nm to 3 microns in thickness.

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 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: Methods of removing native oxide layers and depositing dielectric layers having a controlled number of active sites on MEMS devices for biological applications are disclosed. In one aspect, a method includes removing a native oxide layer from a surface of the substrate by exposing the substrate to one or more ligands in vapor phase to volatize the native oxide layer and then thermally desorbing or otherwise etching the volatized native oxide layer. In another aspect, a method includes depositing a dielectric layer selected to provide a controlled number of active sites on the surface of the substrate. In yet another aspect, a method includes both removing a native oxide layer from a surface of the substrate by exposing the substrate to one or more ligands and depositing a dielectric layer selected to provide a controlled number of active sites on the surface of the substrate.

Abstract: Apparatus and systems are disclosed for providing a protective material for a showerhead of a processing system. In an embodiment, a processing system includes a processing chamber for processing substrates and a showerhead having a diffuser plate for distributing processing gases to the processing chamber. The diffuser plate may include a protective material to protect the showerhead from processing gases. The diffuser plate may be formed with tungsten or tungsten coated with a tantalum alloy and tantalum.

Abstract: The present disclosure relates to a method of depositing a polymer layer, including: providing a substrate, having a sensor structure disposed on the substrate, to a substrate support within a hot wire chemical vapor deposition (HWCVD) chamber; providing a process gas comprising an initiator gas and a monomer gas and a carrier gas to the HWCVD chamber; heating a plurality of filaments disposed in the HWCVD chamber to a first temperature sufficient to activate the initiator gas without decomposing the monomer gas; and exposing the substrate to initiator radicals from the activated initiator gas and to the monomer gas to deposit a polymer layer atop the sensor structure.

Abstract: A method of depositing a high quality low defect single crystalline Group III-Nitride film. A patterned substrate having a plurality of features with inclined sidewalls separated by spaces is provided. A Group III-Nitride film is deposited by a hydride vapor phase epitaxy (HVPE) process over the patterned substrate. The HVPE deposition process forms a Group III-Nitride film having a first crystal orientation in the spaces between features and a second different crystal orientation on the inclined sidewalls. The first crystal orientation in the spaces subsequently overgrows the second crystal orientation on the sidewalls and in the process turns over and terminates treading dislocations formed in the first crystal orientation.

Abstract: In one embodiment, an apparatus includes a first gas distribution assembly that includes a first gas passage for introducing a first process gas into a second gas passage that introduces the first process gas into a processing chamber and a second gas distribution assembly that includes a third gas passage for introducing a second process gas into a fourth gas passage that introduces the second process gas into the processing chamber. The first and second gas distribution assemblies are each adapted to be coupled to at least one chamber wall of the processing chamber. The first gas passage is shaped as a first ring positioned within the processing chamber above the second gas passage that is shaped as a second ring positioned within the processing chamber. The gas distribution assemblies may be designed to have complementary characteristic radial film growth rate profiles.