Abstract: An airfoil includes an airfoil section that defines an airfoil profile. The airfoil section includes a core structure and a hollow panel adjacent to the core structure. The hollow panel forms at least a portion of a leading end of the airfoil profile.

Abstract: An airfoil includes an airfoil section defining an airfoil profile, the airfoil section including a core structure and a plurality of rods disposed adjacent the core structure.

Abstract: An airfoil includes an airfoil section that defines an airfoil profile, and a first endwall section with which the airfoil section is attached. First and second airfoil pieces form different portions of the airfoil profile. The first and second airfoil pieces include respective first ends. The first ends interlock with the first endwall section such that the first and second airfoil pieces are retained with the first endwall section.

Abstract: An airfoil includes an airfoil section that has radially inner and outer ends and defines an airfoil profile. The airfoil profile has a leading end, a trailing end, a suction side, and a pressure side. The airfoil section includes a ceramic airfoil piece that defines a portion of the airfoil profile. The ceramic airfoil piece includes an exterior wall that has an internal cooling circuit.

Abstract: A method of fabricating a ceramic turbine engine article includes building a wall of the article from preceramic layers, wherein the building includes arranging the preceramic layers around one or more sacrificial core elements, converting the preceramic layers to ceramic, and removing the one or more sacrificial core elements to leave one or more cavities in the wall.

Abstract: An airfoil includes an airfoil section that defines an airfoil profile. The airfoil section includes a panel that forms a portion of the airfoil profile and a core structure to which the panel is secured.

Abstract: An airfoil includes a core structure that has an airfoil portion that defines at least a portion of an airfoil profile. The airfoil portion has first and second opposed ends. A support wall extends from the first end. An endwall panel is attached to the support wall adjacent the airfoil portion.

Abstract: An airfoil includes an airfoil section that defines an airfoil profile. The airfoil section includes a distinct panel that forms a portion of the airfoil profile. The panel has a geometrically segmented coating section. The geometrically segmented coating section includes a wall that has an outer side. The outer side includes an array of cells, and there is a coating disposed in the array of cells.

Abstract: An airfoil includes an airfoil section that defines an airfoil profile. A first endwall piece includes a first cup portion that defines a first cavity. A second endwall piece includes a second cup portion that defines a second cavity and an airfoil wall portion that projects from the second cup portion. The airfoil wall portion forms a portion of the airfoil profile of the airfoil section. An airfoil piece defines another portion of the airfoil profile. The airfoil piece has first and second ends. The first end is disposed in the first cavity and the second end is disposed in the second cavity such that the airfoil piece is trapped between the first endwall piece and the second endwall piece.

Abstract: Aspects of the disclosure are directed to a brush seal comprising: a first plate, a wire mesh adjacent the first plate, a bristle pack adjacent the wire mesh, and a second plate adjacent the bristle pack. Aspects of the disclosure are directed to a method comprising: positioning a wire mesh adjacent to a first plate, positioning a bristle pack adjacent to the wire mesh, positioning a second plate adjacent to the bristle pack, applying a toolset to hold the first plate, the wire mesh, the bristle pack, and the second plate in a stack-up, and performing an operation to form a brush seal from the stack-up of the first plate, the wire mesh, the bristle pack, and the second plate.

Abstract: Aspects of the disclosure are directed to a seal configured to interface with at least a first component and a second component of a gas turbine engine. A method for forming the seal includes obtaining an ingot of a fine grained, or a coarse grained, or a columnar grained or a single crystal material from a precipitation hardened nickel base superalloy containing at least 40% by volume of the precipitate of the form Ni3(Al, X), where X is a metallic or refractory element, and processing the ingot to generate a sheet of the material, where the sheet has a thickness within a range of 0.010 inches and 0.050 inches inclusive.

Abstract: A sensor assembly includes a first structure and a second structure disposed radially outwardly of the first structure. Also included is a sensor body extending through the first and second structures, the sensor body having first and second ends, the first end disposed proximate a first environment defined by the first structure and the second end located radially outwardly of the second structure. Further included is a first sealing assembly configured to operatively couple the sensor body to the second structure and to accommodate movement of the sensor body. Yet further included is a position sensor operatively coupled to the sensor body, the position sensor configured to determine a position of a target located within the first interior volume. Also included is at least one biasing member in contact with the target to bias the target into constant operative contact with the sensor body.

Abstract: A gas turbine engine with an adjustable vane includes a platform with a hole and an aperture. A vane is supported for rotation relative to the platform by a trunion that is received in the hole. The vane has an opening that is laterally spaced from the trunion and is in alignment with the aperture. The vane includes an airfoil with a cooling passage in fluid communication with the opening.

Abstract: A gas turbine engine component includes an outer diameter endwall, an inner diameter endwall spaced radially inward of the outer diameter endwall, and at least one body supported between the outer and inner endwalls for rotation about an axis. The body includes an outer diameter surface spaced from the outer diameter endwall by a first gap and an inner diameter surface spaced from the inner diameter endwall by a second gap. The outer and inner diameter surfaces and the outer and inner diameter endwalls are configured such that the first and second gaps remain generally constant in size as the body rotates about the axis.

Abstract: A variable area turbine arrangement according to an exemplary aspect of the present disclosure includes, among other things, a variable vane assembly and a secondary flow system associated with the variable vane assembly. Flow modulation of a cooling fluid through the secondary flow system is changed simultaneously with actuation of the variable vane assembly.

Abstract: A variable area turbine arrangement according to an exemplary aspect of the present disclosure includes, among other things, a first turbine section having at least a first variable vane row and a second turbine section downstream from the first turbine section and having at least a second variable vane row. A transition duct is disposed between the first turbine section and the second turbine section.

Abstract: A sensor assembly includes a first structure and a second structure disposed radially outwardly of the first structure. Also included is a sensor body extending through the first and second structures, the sensor body having first and second ends, the first end disposed proximate a first environment defined by the first structure and the second end located radially outwardly of the second structure. Further included is a first sealing assembly configured to operatively couple the sensor body to the second structure and to accommodate movement of the sensor body. Yet further included is a position sensor operatively coupled to the sensor body, the position sensor configured to determine a position of a target located within the first interior volume. Also included is at least one biasing member in contact with the target to bias the target into constant operative contact with the sensor body.

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a shell defining an interior, a spar extending into the interior and a first flange attached to the spar. The spar is configured to pivot to change a positioning of the shell.

Abstract: An assembly for a turbine engine includes a plurality of vane segments. The vane segments are fastened together and form an adjustable stator vane that pivots about a variable vane axis. The adjustable stator vane includes a stator vane body, a shaft and a flange. The stator vane body extends axially between a first end and a second end, and includes an airfoil, a body surface and a cavity. The body surface is located at the first end. The cavity extends axially from an inlet in the body surface and into the airfoil. The shaft extends along the variable vane axis from the first end. The flange extends circumferentially at least partially around the inlet, and radially from the stator vane body. A first of the vane segments includes the flange. A second of the vane segments includes at least a portion of the airfoil.

Abstract: An adjustable stator vane for a turbine engine includes a shaft, a flange and a stator vane body that pivots about a variable vane axis. The stator vane body extends axially between a first end and a second end. The stator vane body includes an airfoil, a cavity, and a body surface located at the first end. The cavity extends axially from an inlet in the body surface and into the airfoil. The shaft extends along the variable vane axis from the first end. The flange extends circumferentially around the inlet and the shaft, and radially from the stator vane body.