Electrolyte for a solid-state battery includes a body having grains of inorganic material sintered to one another, where the grains include lithium. The body is thin, has little porosity by volume, and has high ionic conductivity.

Electrolyte for a solid-state battery includes a body having grains of inorganic material sintered to one another, where the grains include lithium. The body is thin, has little porosity by volume, and has high ionic conductivity.

A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.

A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.

A ceramic component is provided that is suitable to be placed in high temperature environment. The component includes a first member that is formed of a first material, and a ceramic layer that is bonded to a surface of the first member, which is a side exposed to the high temperature environment and that is formed of a ceramic material having a higher heat resistance than that of the first member. A bonding portion between the first member and the ceramic layer is formed of a composite material having the first material and the ceramic material, and a gradient composition in which an abundance ratio of the first material gradually decreases and an abundance ratio of the ceramic material gradually increases in a direction from the first member to the ceramic layer.

A ceramic component is provided that is suitable to be placed in high temperature environment. The component includes a first member that is formed of a first material, and a ceramic layer that is bonded to a surface of the first member, which is a side exposed to the high temperature environment and that is formed of a ceramic material having a higher heat resistance than that of the first member. A bonding portion between the first member and the ceramic layer is formed of a composite material having the first material and the ceramic material, and a gradient composition in which an abundance ratio of the first material gradually decreases and an abundance ratio of the ceramic material gradually increases in a direction from the first member to the ceramic layer.

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.

Gypsum panels, sheathing systems, and methods of making and using the same are provided. A gypsum panel includes a gypsum core associated with a first fiberglass mat having a continuous barrier coating, the coating penetrating a portion of the first fiberglass mat opposite the gypsum core, wherein gypsum penetrates a remaining fibrous portion of the first fiberglass mat such that voids in the first fiberglass mat are substantially eliminated. A building sheathing system includes at least two gypsum panels and a seaming component to provide a seam at an interface between the gypsum panels.

A method of manufacturing an article containing silicon carbide as a main component includes a step of laying raw material powder, and a step of irradiating the raw material powder with a laser beam, wherein the raw material powder contains 95 mol % or more of silicon carbide, and wherein, in the step of irradiating the raw material powder with the laser beam, the raw material powder is irradiated with the laser beam to decompose the silicon carbide in at least a part of an irradiation portion of the laser beam into silicon and carbon and to turn the silicon or the carbon into melt.