Applied Materials, Inc.

Other

Yuriy Melnik

Sukti Chatterjee

Pravin K Narwankar

David Alexander Britz

Lance A Scudder

Olga Kryliouk

David P Thompson

Tetsuya Ishikawa

Thomas Knisley

Hidehiro Kojiri

Son Truong Nguyen

Lily L Pang

Kenichi Ohno

Mark Joseph Saly

Anzhong Chang

David H Quach

Lu Chen

Harsukhdeep S Ratia

Jonathan Stuart Frankel

Kaushal Gangakhedkar

Rami Hourani

David Masayuki Ishikawa

Colin Costano Neikirk

Jie Su

Andrew Ceballos

Amita Joshi

Jeffrey W Anthis

Sandeep Nijhawan

Brian Hayes Burrows

Ranga Rao Arnepalli

Eric H Liu

Anand Vasudev

Eda Tuncel

Suresh Chand Seth

Tuoh-Bin Ng

Vibhas Singh

Exemplary methods of forming a coating of material on a substrate may include forming a plasma of a first precursor and an oxygen-containing precursor. The first precursor and the oxygen-containing precursor may be provided in a first flow rate ratio. The methods may include depositing a first layer of material on the substrate. While maintaining the plasma, the methods may include adjusting the first flow rate ratio to a second flow rate ratio. The methods may include depositing a second layer of material on the substrate.

Method for forming plasma coating

Embodiments of the present disclosure generally relate to densified nanoimprint films and processes for making these densified nanoimprint films, as well as optical devices containing the densified nanoimprint films. In one or more embodiments, a densified nanoimprint film contains a base nanoimprint film and a metal oxide disposed on the base nanoimprint film and in between the nanoparticles. The base nanoimprint film contains nanoparticles, where the nanoparticles contain titanium oxide, zirconium oxide, niobium oxide, tantalum oxide, hafnium oxide, chromium oxide, indium tin oxide, silicon nitride, or any combination thereof. The metal oxide contains aluminum oxide, titanium oxide, zirconium oxide, niobium oxide, tantalum oxide, indium oxide, indium tin oxide, hafnium oxide, chromium oxide, scandium oxide, tin oxide, zinc oxide, yttrium oxide, praseodymium oxide, magnesium oxide, silicon oxide, silicon nitride, silicon oxynitride, or any combination thereof.

Methods for increasing the density of high-index nanoimprint lithography films

Exemplary backpressure monitoring apparatuses may include a fluid supply source having a fluid port. The backpressure monitoring apparatuses may include a flow control mechanism fluidly coupled with the fluid port. The backpressure monitoring apparatuses may include a delivery tube fluidly coupled with the flow control mechanism and the fluid port. The backpressure monitoring apparatuses may include a pressure differential gauge fluidly coupled with the delivery tube. The pressure differential gauge may include an interface mechanism that is engageable with an outlet of a fluid flow device.

Backpressure monitoring apparatus

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.

Protection of components from corrosion

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.

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.

Methods of protecting aerospace components against corrosion and oxidation

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.

Methods for depositing sacrificial coatings on aerospace components

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.

Method, materials and process for native oxide removal and regrowth of dielectric oxides for better biosensor performance

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 depositing coatings on aerospace components

Embodiments of the present disclosure generally relate to protective coatings on various substrates including aerospace components and methods for depositing the protective coatings. In one or more embodiments, a method of forming a protective coating on an aerospace component includes forming an aluminum oxide layer on a surface of the aerospace component and depositing a boron nitride layer on or over the aluminum oxide layer during a vapor deposition process. In some examples, the method includes depositing a metal-containing catalytic layer on the aluminum oxide layer before depositing the boron nitride layer. The boron nitride layer can include hexagonal boron nitride (hBN).

Nitride protective coatings on aerospace components and methods for making the same

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.

Methods for forming protective coatings containing crystallized aluminum oxide

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.

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.

Growing community of inventors

San Jose, CA, United States of America

Yuriy Melnik