Abstract: An airfoil includes an airfoil section that defines a trailing edge region that includes a trailing edge. The airfoil section is formed of a ceramic matrix composite that includes core fiber plies and skin fiber plies. The core fiber plies define a radial tube that has a radiused end in the trailing edge region. The skin fiber plies wrap around the core fiber plies and a filler element in the trailing edge region is aft of the internal cavity and is sandwiched between the skin fiber plies on the pressure side and the skin fiber plies on the suction side. There is at least one cooling passage that includes a first, inlet orifice section that opens to the internal cavity at a location forward of the radiused end and that extends through the core fiber plies, and a second, outlet orifice section that extends through the trailing edge.

Abstract: A method of forming a ceramic matrix composite (CMC) vane including an inner diameter platform, an outer diameter platform, and an airfoil extending between the inner diameter platform and the outer diameter platform includes laying up a ceramic preform by arranging at least one core formed from a first ceramic material, and laying up, over the at least one ceramic core, a plurality of contoured plies, each of the plurality of contoured plies formed from a second ceramic material. Each of the plurality of contoured plies partially forms the inner diameter platform, the outer diameter platform, and the airfoil of the vane. The method further includes densifying the ceramic preform with a matrix.

Abstract: Systems and methods are disclosed for producing a hollow composite part, such as a CMC airfoil, using a segmented mandrel formed of individual mandrel segments. The individual mandrel segments may be dimensioned to permit extraction from highly twisted and/or curved parts.

Abstract: A method of reinforcing a ceramic sandwich structure includes forming a ceramic core, assembling the sandwich structure by disposing the core between and in physical contact with a first panel and a second panel, and weaving a plurality of z-fibers at least partially through a thickness of the sandwich structure.

Abstract: A method of fabricating a seal arc segment includes laying-up at least one radially inner-most ceramic fabric ply on a mandrel, laying-up the at least one discontinuous radially intermediate ceramic fabric ply on the at least one inner-most ceramic fabric ply, the at least one discontinuous radially intermediate ceramic fabric ply having cutout voids, laying-up at least one radially outer-most ceramic fabric ply on the at least one discontinuous radially intermediate ceramic fabric ply with the cutout voids, the radially inner-most ceramic fabric ply, the at least one discontinuous radially intermediate ceramic fabric ply, and the radially outer-most ceramic fabric ply together providing a seal arc segment fiber preform, and densifying the seal arc segment fiber preform with a ceramic matrix material to form a seal arc segment wall of a seal arc segment, wherein the cutout voids define cooling channels in the seal arc segment wall.

Abstract: A combined gas turbine engine vane and blade outer air seal assembly includes a vane having an airfoil extending from the leading edge to a trailing edge, and has an outer platform. The outer platform has a cooling channel that extends into the airfoil to receive cooling air. The outer platform extends to an integral blade outer air seal to be positioned radially outwardly of a turbine blade in a gas turbine engine. At least a portion of the vane and the blade outer air seal are formed of ceramic matrix composite materials. A gas turbine engine is also disclosed.

Abstract: A method of forming a ceramic matrix composite (CMC) vane including an inner diameter platform, an outer diameter platform, and an airfoil extending between the inner diameter platform and the outer diameter platform includes laying up a ceramic preform by arranging at least one core formed from a first ceramic material, and laying up, over the at least one ceramic core, a plurality of contoured plies, each of the plurality of contoured plies formed from a second ceramic material. Each of the plurality of contoured plies partially forms the inner diameter platform, the outer diameter platform, and the airfoil of the vane. The method further includes densifying the ceramic preform with a matrix.

Abstract: A method of fabricating a ceramic matrix composite component includes fabricating a ceramic preform, the preform comprising a hollow portion with an internal cavity extending along a first axis from a first end to a second end of the hollow portion, supporting the hollow portion with an auxetic mandrel disposed within and the internal cavity and coaxial with the hollow portion, the auxetic mandrel comprising a first mandrel end and a second mandrel end, at least partially densifying the preform with a matrix, and removing the auxetic mandrel from the internal cavity by simultaneously applying a compressive force to each of the first mandrel end and the second mandrel end creating a deformed auxetic mandrel to reduce a cross-sectional profile of the auxetic mandrel along a second axis orthogonal to the first axis, and extracting the deformed auxetic mandrel from the first end of the hollow portion.

Abstract: A combined gas turbine engine vane and blade outer air seal assembly includes a vane having an airfoil extending from the leading edge to a trailing edge, and has an outer platform. The outer platform has a cooling channel that extends into the airfoil to receive cooling air. The outer platform extends to an integral blade outer air seal to be positioned radially outwardly of a turbine blade in a gas turbine engine. At least a portion of the vane and the blade outer air seal are formed of ceramic matrix composite materials. A gas turbine engine is also disclosed.

Abstract: A gas turbine engine component includes an inner surface and an outer surface. The outer surface and the inner surface are formed of ceramic matrix composite layers, and mount member. The mount member is in contact with an insert that is inserted within outer layers of the outer platform to form a thickened portion having an end surface that will react against forces from the mount member. A gas turbine engine and a method are also disclosed.

Abstract: An airfoil for a gas turbine engine includes an airfoil section and a platform that has a non-gaspath side, a flange that extends from the non-gaspath side, and a gaspath side from which the airfoil section extends. The flange is comprised of a sandwich composite that includes first and second ceramic matrix composite (CMC) skins that each have at least one 2-D ceramic fiber ply, and a cellular core disposed between the first and second CMC skins.

Abstract: An airfoil includes a platform and an airfoil section that are formed of a ceramic matrix composite that includes core fiber plies, skin fiber plies, platform fiber plies, and a cooling passage that extends through selected ones of the plies to provide a cooling circuit through the airfoil section and into the platform.

Abstract: A gas turbine engine component includes an inner surface and an outer surface. The outer surface and the inner surface are formed of ceramic matrix composite layers, and mount member. The mount member is in contact with an insert that is inserted within outer layers of the outer platform to form a thickened portion having an end surface that will react against forces from the mount member. A gas turbine engine and a method are also disclosed.

Abstract: A method of forming a ceramic matrix composite (CMC) vane including an inner diameter platform, an outer diameter platform, and an airfoil extending between the inner diameter platform and the outer diameter platform includes laying up a ceramic preform by arranging at least one core formed from a first ceramic material, and laying up, over the at least one ceramic core, a plurality of contoured plies, each of the plurality of contoured plies formed from a second ceramic material. Each of the plurality of contoured plies partially forms the inner diameter platform, the outer diameter platform, and the airfoil of the vane. The method further includes densifying the ceramic preform with a matrix.

Abstract: A method of forming a ceramic matrix composite (CMC) vane including an inner diameter platform, an outer diameter platform, and an airfoil extending between the inner diameter platform and the outer diameter platform includes laying up a ceramic preform by arranging at least one core formed from a first ceramic material, and laying up, over the at least one ceramic core, a plurality of contoured plies, each of the plurality of contoured plies formed from a second ceramic material. Each of the plurality of contoured plies partially forms the inner diameter platform, the outer diameter platform, and the airfoil of the vane. The method further includes densifying the ceramic preform with a matrix.

Abstract: A gas turbine engine stator vane combination includes a stator vane body having an airfoil with a leading edge, a trailing edge, a suction side and a pressure side, and having at least one internal cooling channel. The stator vane body is formed of ceramic matrix composite materials. A spar is received within the at least one cooling air channel and formed of a metal. The spar has an outer peripheral surface spaced from an inner peripheral surface of the cooling air channel to define a cooling air path, with the cooling air path having a varying cross-sectional area through the cooling air channel. A gas turbine engine is also disclosed.

Abstract: A combined gas turbine engine vane and blade outer air seal assembly includes a vane having an airfoil extending from the leading edge to a trailing edge, and has an outer platform. The outer platform has a cooling channel that extends into the airfoil to receive cooling air. The outer platform extends to an integral blade outer air seal to be positioned radially outwardly of a turbine blade in a gas turbine engine. At least a portion of the vane and the blade outer air seal are formed of ceramic matrix composite materials. A gas turbine engine is also disclosed.

Abstract: A combustor includes a combustion chamber and a liner that bounds at least a portion of the combustion chamber. The liner includes a first side facing the combustion chamber and a second side facing away from the combustion chamber. The liner is formed of a lay-up of ceramic matrix composite (CMC) plies that have a first CMC ply on the first side, a second CMC ply on the second side, and intermediate CMC plies between the first and second CMC plies. At least one of the intermediate CMC plies has a pattern of voids that define cooling channels in the combustor panel. The cooling channels are bound on lateral channel sides by the at least one of the intermediate CMC plies.

Abstract: An airfoil includes a platform and an airfoil section that are formed of a ceramic matrix composite that includes core fiber plies, skin fiber plies, platform fiber plies, and a cooling passage that extends through selected ones of the plies to provide a cooling circuit through the airfoil section and into the platform.

Abstract: An airfoil includes a platform and an airfoil section. The airfoil section and the platform are formed of a ceramic matrix composite (CMC) having fiber plies and a ceramic matrix, the fiber plies include first and second groups of core fiber plies that respectively define first and second radial tubes that circumscribe first and second internal cavities in the airfoil section. Skin fiber plies define an exterior of the airfoil section, wrap around the first and second groups of core fiber plies, and flare outwardly through a fillet into the platform. Platform fiber plies extend in the platform adjacent the skin fiber plies. There is at least one closed-circuit cooling passage defined in the fiber plies. The cooling passage initiates from the first internal cavity, extends within the platform, and ends at the second internal cavity.