Airfoils for gas turbine engines are provided. In one embodiment, an airfoil formed from a ceramic matrix composite material includes opposite pressure and suction sides extending radially along a span and defining an outer surface of the airfoil. The airfoil also includes opposite leading and trailing edges extending radially along the span. The pressure and suction sides extend axially between the leading and trailing edges. The leading edge defines a forward end of the airfoil, and the trailing edge defining an aft end of the airfoil. Further, the airfoil includes a trailing edge portion defined adjacent the trailing edge at the aft end of the airfoil; a plenum defined within the airfoil forward of the trailing edge portion; and a cooling passage defined within the trailing edge portion proximate the suction side. Methods for forming airfoils for gas turbine engines also are provided.

Described herein are a bonded ceramic having a channel through which a fluid can flow, and a method for manufacturing the same. The bonded ceramic includes: a first ceramic base material; and a second ceramic base material, wherein: the first ceramic base material and the second ceramic base material are bonded by adhesive layer-free bonding; a pattern is formed on either or both of the bonding surface of the first ceramic base material where the first ceramic base material comes in contact with the second ceramic base material and the bonding surface of the second ceramic base material where the second ceramic base material comes in contact with the first ceramic base material; and the bonded ceramic includes pores having a size of 0.01 m to 50 m and formed along the bonding surface between the first ceramic base material and the second ceramic base material.

Provided is a composite substrate which is provided with: a single crystal silicon carbide thin film 11 having a thickness of 1m or less; a handle substrate 12 which supports the single crystal silicon carbide thin film 11 and is formed from a heat-resistant material (excluding single crystal silicon carbide) having a heat resistance of not less than 1,100 C.; and an intervening layer 13 which has a thickness of 1m or less and is arranged between the single crystal silicon carbide thin film 11 and the handle substrate 12, and which is formed from at least one material selected from among silicon oxide, silicon nitride, aluminum oxide, aluminum nitride, zirconium oxide, silicon and silicon carbide, or from at least one metal material selected from among Ti, Au, Ag, Cu, Ni, Co, Fe, Cr, Zr, Mo, Ta and W. This composite substrate according to the present invention enables the formation of a nanocarbon film having few defects at low cost.

A transaction card includes a monolithic ceramic card body having one or more pockets, and at least one of a magnetic stripe, a barcode, and a laser signature portion. The one or more pockets may be configured to receive at least one of the magnetic stripe, the barcode, a contact chip module, a contactless chip module, a dual interface chip module, a booster antenna, a hologram or commercial indicia. A transaction card may also include a substrate layer having a first side and a second side. A first ceramic layer is connected to the first side of the substrate layer.

A wavelength conversion member complex includes a wavelength conversion member, a joining material, and a heat dissipation member. The wavelength conversion member includes a support and a phosphor member. The support defines a through-hole extending from an upper surface to a lower surface. The support has a concave portion on the lower surface around the through-hole. The concave portion is spaced apart from the through-hole. The phosphor member is disposed in the through-hole and includes a phosphor. The lower surface of the phosphor member is continuous with the lower surface of the support. The joining material is disposed in the concave portion, and has a lower surface that is flush with the lower surface of the support. The heat dissipation member is disposed under the joining material and the phosphor member, and has an upper surface in contact with the lower surface of the joining material.

Reinforced concrete structures and assemblies, building systems, and methods of fabrication.

A floor element for forming a floor covering, wherein the floor element comprises: a decorative layer made of a ceramic material; a support layer arranged below the decorative layer; and an intermediate layer comprising a rigid resin material that permeates a lower surface of the decorative layer, wherein the decorative layer is between 8 and 10 mm thick, wherein the support layer is made of rigid PVC, comprises more than 30 wt % of filler material and is less than 6 mm thick, and wherein the floor element comprises an intermediate reinforcing layer having a resin material that permeates a lower surface of the decorative layer, wherein the intermediate reinforcing layer is an adhesive layer that bonds together the decorative layer and the support layer.

A means for attaching a metallic component to a non-metallic component using a compliant material having thermal properties intermediate those of the metallic component to a non-metallic component is provided. The method can accommodate CTE mismatches and wear-type problems common to many assemblies of dissimilar materials. In particular, the method provides a sufficient wear surface to accommodate relative motion and provide a durable wear surface that does not excessively wear/gall/mico-weld itself together and provides the necessary damping and motion for proper operation in aeronautical applications.

To provide a production method that enables to produce a gas barrier film having excellent transparency and gas barrier properties at high speed. A method for producing a gas barrier film, the gas barrier film having an inorganic thin-film layer laminated to at least one of surfaces of a polymer substrate, in which the inorganic thin-film layer is formed by a vacuum vapor-deposition method using Al and SiO.sub.2 as vapor-deposition materials while introducing oxygen gas.

A method of preparing a ceramic matrix composite (CMC) component that includes a protective ceramic layer comprises adhering at least one flexible ceramic tape to a ceramic fiber preform, where the at least one flexible ceramic tape comprises ceramic particles dispersed in an organic binder phase. After the adhering, the at least one flexible ceramic tape is heated to a temperature sufficient to volatilize the organic binder phase, thereby forming a porous ceramic layer on at least a portion of the ceramic fiber preform. After the heating and volatilizing, the ceramic fiber preform and the porous ceramic layer are infiltrated with a molten material, thereby forming a CMC component including, on at least a portion thereof, a protective ceramic layer.