the absorbent sheet for pets which can suppress the outflow of a functional material is provided. An absorbent sheet (10) for pets includes a topsheet (12), a backsheet (14), an absorber (20) provided between the topsheet and the backsheet, a functional (40) material, and a recess (50)that is recessed in a direction from the topsheet toward the backsheet. The functional material (40) is provided at a position of the recess (50).

A light extraction substrate for an organic light-emitting device (OLED) which can improve the brightness of a display or an illumination system to which an OLED is applied by improving light extraction efficiency and a method of manufacturing the same. The light extraction substrate for an OLED includes an oxide or nitride thin film formed on a substrate body. The oxide or nitride thin film includes a base layer formed on the substrate body, a first texture formed on the base layer, the first texture having a plurality of first protrusions which protrude continuously or discontinuously from the base layer, and a second texture having a plurality of second protrusions which protrude continuously or discontinuously from each outer surface of the first protrusions.

This application relates to an enclosure for a portable electronic device. The enclosure includes an aluminum alloy substrate and an anodized layer overlaying and formed from the aluminum alloy substrate, wherein the anodized layer has an external surface that has a concentration of zinc that is between about 3 wt % to about 7 wt %.

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.

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.

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.

An article including a durable, optically transparent, and superhydrophobic coating is described. In one aspect, the present disclosure provides an article comprising a substrate, and disposed adjacent the substrate, a layer comprising graphitic carbon, diamond-like carbon, and aerogel. In another aspect, the present disclosure provides a method for preparing a coated substrate, comprising providing a carbon layer disposed on a substrate and having a textured surface; and disposing aerogel adjacent to at least a portion of the textured surface.

A watercraft matting is described that includes a bottom surface configured to come into contact with a watercraft surface, a top surface having a plurality of recessed portions disposed between a plurality of protruding portions, where the protruding portions being formed of a non-skid material, and a phosphorescent material positioned within the plurality of recessed portions. The phosphorescent material is adapted to glow-in-the-dark when exposed to an ultraviolet light. The plurality of protruding portions may be formed of a cross-linked-closed-cell (CLCC) foam material.

Building panels, especially floor panels, and a method of forming embossed in register surfaces with a digital ink head that applies a curable ink on the panel surface or on an upper side of a foil as a coating and forms an ink matrix that is used to create a cavity in the surface by applying a pressure on the ink matrix.

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.