Abstract: 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.

Abstract: Embodiments of the present disclosure generally relate to protective coatings on an aerospace component and methods for depositing the protective coatings. The protective coating can be anti-coking coatings to reduce or suppress coke formation when the aerospace component is heated in the presence of a fuel. In one or more embodiments, a method for depositing the protective coating on an aerospace component includes exposing the aerospace component to a cleaning process to produce a cleaned surface on the aerospace component and sequentially exposing the aerospace component to a precursor and a reactant to form a protective coating on the cleaned surface of the aerospace component by an atomic layer deposition (ALD) process. The aerospace component can be one or more of a fuel nozzle, a combustor liner, a combustor shield, a heat exchanger, a fuel line, a fuel valve, or any combination thereof.

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: 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: 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: 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.

Abstract: A method for detecting corrosion on a conductive object includes submerging a surface of the conductive object at least partially in an aqueous solution, flowing current through the surface of the conductive object by forming a voltage differential across the surface, varying the voltage differential across the surface while monitoring the current through the surface of the conductive object, determining a total charge corresponding to a corrosion level of the surface of the conductive object based on current versus voltage levels. The corrosion level may further be utilized in selecting a cleaning process to remediate the corrosion of the surface based on the corrosion level and in applying a protective corrosion barrier to on at least part of the surface after the cleaning process.

Abstract: Plasma is generated in a semiconductor process chamber by a plurality of microwave inputs with slow or fast rotation. Radial uniformity of the plasma is controlled by regulating the power ratio of a center-high mode and an edge-high mode of the plurality of microwave inputs into a microwave cavity. The radial uniformity of the generated plasma in a plasma chamber is attained by adjusting the power ratio for the two modes without inputting time-splitting parameters for each mode.

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: A method for detecting corrosion on a conductive object includes submerging a surface of the conductive object at least partially in an aqueous solution, flowing current through the surface of the conductive object by forming a voltage differential across the surface, varying the voltage differential across the surface while monitoring the current through the surface of the conductive object, determining a total charge corresponding to a corrosion level of the surface of the conductive object based on current versus voltage levels. The corrosion level may further be utilized in selecting a cleaning process to remediate the corrosion of the surface based on the corrosion level and in applying a protective corrosion barrier to on at least part of the surface after the cleaning 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, and is from 1 nm to 3 microns in thickness.

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. The protective coating can be anti-coking coatings to reduce or suppress coke formation when the aerospace component is heated in the presence of a fuel. In one or more embodiments, a method for depositing the protective coating on an aerospace component includes exposing the aerospace component to a cleaning process to produce a cleaned surface on the aerospace component and sequentially exposing the aerospace component to a precursor and a reactant to form a protective coating on the cleaned surface of the aerospace component by an atomic layer deposition (ALD) process. The aerospace component can be one or more of a fuel nozzle, a combustor liner, a combustor shield, a heat exchanger, a fuel line, a fuel valve, 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 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: 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.