Abstract: Methods for providing an inorganic oxide coating to high aspect ratio particles containing an active pharmaceutical ingredient are described as are compositions containing such coated particles.

Abstract: This disclosure pertains to coated drug compositions and methods of preparing coated drug compositions with a low temperature o-zone based silicon oxide coating. Specifically, the instant application discloses a method to coat active pharmaceutical ingredient particles using a silicon precursor and ozone at a low temperature.

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: 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, an aerospace component has a body containing a nickel superalloy, a metal oxide template layer disposed on the body, and an aluminum oxide layer disposed between the body of the aerospace component and the metal oxide template layer. The metal oxide template layer contains chromium oxide, chromium oxide hydroxide, or a combination thereof. The aluminum oxide layer contains ?-Al2O3. The metal oxide template layer and the aluminum oxide layer have a corundum crystal structure and have crystal structures with a lattice mismatch of about 0.1% to about 10%.

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.

Abstract: A reactor for coating particles includes a stationary vacuum chamber that has a lower portion that forms a half-cylinder and an upper portion and that holds a bed of particles to be coated, a vacuum port in the upper portion of the chamber, a paddle assembly, and a gas injection assembly that includes a vaporizer to convert a first liquid to a first reactant or precursor gas, a manifold to receive the first reactant or precursor gas from the vaporizer, and a plurality of channels leading from the manifold to a plurality of apertures located in the lower portion of the chamber.

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 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: 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 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: 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: This disclosure pertains to coated drug compositions and methods of preparing coated drug compositions with a low temperature silicon oxide coating. Specifically, the instant application discloses a method to coat active pharmaceutical ingredient particles using a silicon precursor and a catalyst at a low temperature.

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: 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.

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 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: 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.

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.