An airfoil for a gas turbine engine is provided that includes a first portion formed from a first plurality of plies of a ceramic matrix composite material and defining an inner surface of the airfoil, as well as a second portion formed from a second plurality of plies of a ceramic matrix composite material and defining an outer surface of the airfoil. The first portion and the second portion define a non-line of sight cooling aperture extending from the inner surface to the outer surface of the airfoil. In one embodiment, a surface angle that is less than 45° is defined between a second aperture and the outer surface. A method for forming an airfoil for a gas turbine engine also is provided.

An airfoil for a gas turbine engine is provided that includes a first portion formed from a first plurality of plies of a ceramic matrix composite material and defining an inner surface of the airfoil, as well as a second portion formed from a second plurality of plies of a ceramic matrix composite material and defining an outer surface of the airfoil. The first portion and the second portion define a non-line of sight cooling aperture extending from the inner surface to the outer surface of the airfoil. In one embodiment, a surface angle that is less than 45° is defined between a second aperture and the outer surface. A method for forming an airfoil for a gas turbine engine also is provided.

A method of forming a ceramic matrix composite component according to an exemplary embodiment of this disclosure, among other possible things includes laying up plies of ceramic reinforcement material with sacrificial plies to form a preform, infiltrating the preform with a ceramic matrix material, and machining away the sacrificial plies to reveal a surface profile of the ceramic matrix composite component. A preform for a ceramic matrix composite component is also disclosed.

A method of forming a ceramic matrix composite component according to an exemplary embodiment of this disclosure, among other possible things includes laying up plies of ceramic reinforcement material with sacrificial plies to form a preform, infiltrating the preform with a ceramic matrix material, and machining away the sacrificial plies to reveal a surface profile of the ceramic matrix composite component. A preform for a ceramic matrix composite component is also disclosed.

Provided are a powder for laser manufacturing which can be stably manufactured and from which a three-dimensional manufactured object ensuring a manufacturing accuracy can be obtained and a using method thereof. A powder for ceramic manufacturing for obtaining a manufactured object by repeatedly sintering or fusing and solidifying in sequence a powder in an irradiation portion with laser light, in which the powder includes a plurality of compositions, at least one composition of the compositions is an absorber that relatively strongly absorbs the laser light compared to other compositions, and at least a part of the absorber changes to a different composition that relatively weakly absorbs the laser light by irradiation with the laser light and a using method of a powder in which the powder is used.

A cathode configured for a solid-state battery includes a body having grains of inorganic material sintered to one another, wherein the grains comprise lithium. A thickness of the body is from 3 μm to 100 μm. The first major surface and the second major surface have an unpolished granular profile such that the profile includes grains protruding outward from the respective major surface with a height of at least 25 nm and no more than 150 μm relative to recessed portions of the respective major surface at boundaries between the respective grains.

A cathode configured for a solid-state battery includes a body having grains of inorganic material sintered to one another, wherein the grains comprise lithium. A thickness of the body is from 3 μm to 100 μm. The first major surface and the second major surface have an unpolished granular profile such that the profile includes grains protruding outward from the respective major surface with a height of at least 25 nm and no more than 150 μm relative to recessed portions of the respective major surface at boundaries between the respective grains.

A hydraulic composition for an additive manufacturing device has an excellent initial flexural strength development property and dimensional stability. The hydraulic composition includes 1.5 to 14 parts by mass of a polymer with respect to 100 parts by mass of an inorganic binder. In addition, in a hydraulic composition for an additive manufacturing device, the inorganic binder may contain 50 to 100 mass % of a calcium aluminate with respect to 100 mass % of the entire inorganic binder, and in a hydraulic composition for an additive manufacturing device the inorganic binder, may contain 0 to 50 mass % of rapid hardening cement with respect to 100 mass % of the entire inorganic binder.

A hydraulic composition for an additive manufacturing device has an excellent initial flexural strength development property and dimensional stability. The hydraulic composition includes 1.5 to 14 parts by mass of a polymer with respect to 100 parts by mass of an inorganic binder. In addition, in a hydraulic composition for an additive manufacturing device, the inorganic binder may contain 50 to 100 mass % of a calcium aluminate with respect to 100 mass % of the entire inorganic binder, and in a hydraulic composition for an additive manufacturing device the inorganic binder, may contain 0 to 50 mass % of rapid hardening cement with respect to 100 mass % of the entire inorganic binder.

A method of manufacturing a ceramic matrix composite (CMC) turbine nozzle shell is provided. The method includes: assembling a primary outer nozzle platform, a primary inner nozzle platform, a core and trailing edge preform, and an airfoil-shaped body; joining the primary outer nozzle platform to a secondary outer nozzle platform of the airfoil-shaped body; and joining the primary inner nozzle platform to a secondary inner nozzle platform of the airfoil-shaped body. Composite plies circumferentially surround the airfoil-shaped body, and their longitudinal edges are cut into fingers that are folded down. The fingers are interleaved between secondary platform plies to form the secondary outer and inner nozzle platforms.