Abstract: A reactor for coating particles includes a vacuum chamber configured to hold particles to be coated, a vacuum port to exhaust gas from the vacuum chamber via the outlet of the vacuum chamber, a chemical delivery system configured to flow a process gas into the particles via a gas inlet on the vacuum chamber, one or more vibrational actuators located on a first mounting surface of the vacuum chamber, and a controller configured to cause the one or more vibrational actuators to generate a vibrational motion in the vacuum chamber sufficient to induce a vibrational motion in the particles held within the vacuum chamber.

Abstract: A method of preparing a pharmaceutical composition having a drug-containing core enclosed by one or more silicon oxide materials is provided. The method entails alternating exposing the particles to gaseous or vaporous SiCl4 and gaseous or vaporous H2O at a reduced temperature and in the absence of a catalyst.

Abstract: A reactor for coating particles includes one or more motors, a rotary vacuum chamber configured to hold particles to be coated, wherein the rotary vacuum chamber is coupled to the motors, a controller configured to cause the motors to rotate the rotary vacuum chamber about an axial axis of the rotary vacuum chamber such that the particles undergo tumbling agitation, a vacuum port to exhaust gas from the rotary vacuum chamber, a paddle assembly including a rotatable drive shaft extending through the rotary vacuum chamber and coupled to the motors and at least one paddle extending radially from the drive shaft, such that rotation of the drive shaft by the motors orbits the paddle about the drive shaft in a second direction, and a chemical delivery system including a gas outlet on the paddle configured inject process gas into the particles.

Abstract: A reactor for coating particles includes a vacuum chamber configured to hold particles to be coated, a vacuum port to exhaust gas from the vacuum chamber via the outlet of the vacuum chamber, a chemical delivery system configured to flow a process gas into the particles via a gas inlet on the vacuum chamber, one or more vibrational actuators located on a first mounting surface of the vacuum chamber, and a controller configured to cause the one or more vibrational actuators to generate a vibrational motion in the vacuum chamber sufficient to induce a vibrational motion in the particles held within the vacuum chamber.

Abstract: A pharmaceutical composition containing a metal oxide coated particle comprising 1) an amorphous solid dispersion (ASD) core containing an active pharmaceutical ingredient (API) and a polymer; and 2) a metal oxide coating, and the method of making said metal oxide coated particle by atomic layer deposition (ALD). The metal oxide coated particle is useful because it prevents the ASD from crystallization and helps maintain the ASD in an amorphous form.

Abstract: A reactor for coating particles includes one or more motors, a rotary vacuum chamber configured to hold particles to be coated and coupled to the motors, a controller configured to cause the motors to rotate the chamber in a first direction about an axial axis at a rotation speed sufficient to force the particles to be centrifuged against an inner diameter of the chamber, a vacuum port to exhaust gas from the rotary vacuum chamber, a paddle assembly including a rotatable drive shaft extending through the chamber and coupled to the motors and at least one paddle extending radially from the drive shaft, such that rotation of the drive shaft by the motors orbits the paddle about the drive shaft in a second direction, and a chemical delivery system including a gas outlet on the paddle configured inject process gas into the particles.

Abstract: A reactor for coating particles includes one or more motors, a rotary vacuum chamber configured to hold particles to be coated, wherein the rotary vacuum chamber is coupled to the motors, a controller configured to cause the motors to rotate the rotary vacuum chamber about an axial axis of the rotary vacuum chamber such that the particles undergo tumbling agitation, a vacuum port to exhaust gas from the rotary vacuum chamber, a paddle assembly including a rotatable drive shaft extending through the rotary vacuum chamber and coupled to the motors and at least one paddle extending radially from the drive shaft, such that rotation of the drive shaft by the motors orbits the paddle about the drive shaft in a second direction, and a chemical delivery system including a gas outlet on the paddle configured inject process gas into the particles.

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: A reactor for coating particles includes a stationary vacuum chamber to hold a bed of particles to be coated, a vacuum port in an upper portion of the chamber, a chemical delivery system configured to inject a reactant or precursor gas into a lower portion of the chamber, a paddle assembly, and a motor to rotate a drive shaft of the paddle assembly. The lower portion of the chamber forms a half-cylinder. The paddle assembly includes a rotatable drive shaft extending through the chamber along the axial axis of the half cylinder, and a plurality of paddles extending radially from the drive shaft such that rotation of the drive shaft by the motor orbits the plurality of paddles about the drive shaft.

Abstract: A method of preparing a pharmaceutical composition having a drug-containing core enclosed by one or more metal oxide materials is provided. The method includes the sequential atomic layer deposition of a metal oxide layer(s) followed by molecular level deposition of a polymer layer(s).

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: A reactor for coating particles includes a stationary vacuum chamber having a lower portion that forms a half-cylinder and an upper portion to hold a bed of particles to be coated, a vacuum port in the upper portion of the chamber, a paddle assembly, a motor to rotate a drive shaft of the paddle assembly, a chemical delivery system to deliver a first fluid, and a first gas injection assembly to receive the first fluid from the chemical delivery system and having apertures configured to inject a first reactant or precursor gas into the lower portion of the chamber and such that the first reactant or precursor gas flows substantially tangent to a curved inner surface of the half-cylinder.

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.