According to one embodiment of this disclosure a core includes a first end and a second end spaced generally opposite from the first end. The core further includes a stacking axis defined between the first end and second end and a first toroidal structure located between the first end and the second end. The first toroidal structure includes a first passage extending through the first toroidal structure in a first direction that is perpendicular to and passes through the stacking axis. The core also includes a second toroidal structure located between the first toroidal structure and the second end. The second toroidal structure includes a second passage extending through the second toroidal structure in a second direction. The first direction and the second direction are oriented along the stacking axis at a non-zero degree angle with respect to each other.

A convergent-divergent nozzle for a turbofan engine of a supersonic aircraft, wherein the nozzle has an inner wall that delimits a flow channel through the nozzle radially outside, wherein the flow channel has a nozzle throat surface and a nozzle exit surface. The inner wall includes a first group of adjustable segments forming an upstream convergent area of the nozzle, and second group of adjustable segments forming a downstream constant/divergent area of the nozzle. It is provided that the segments of the first group or the segments of the second group are curved towards the flow channel in a convex manner at least in an area that adjoins the other group, forming the nozzle throat surface in the area of the convex curvature and adjoining the segments of the respectively other group at an axial distance to the axial position of the nozzle throat surface.

A vane assembly includes a plurality of airfoils that extend from a first end to a second, opposed end. A first platform is at the first end and is joined to the plurality of airfoils. A second platform is at the second end and is joined to the plurality of airfoils. At least one of the first platform, the second platform and the plurality of airfoils include a three-dimensional arrangement of continuous fibers and at least one different one of the first platform, the second platform and the plurality of airfoils include a two-dimensional arrangement of continuous fibers.

An airfoil includes an airfoil piece that defines at least a portion of an airfoil profile. The airfoil piece has a radial end and a first radial slot in the radial end. An end section has a second radial slot adjacent the first radial slot. The first radial slot and the second radial slot together form a radial seal slot. A seal is disposed in the radial seal slot.

An airfoil includes an endwall section and an airfoil section that defines, at least in part, an airfoil profile. At least one of the airfoil section or the endwall section includes a seal cavity, and a seal is disposed in the seal cavity.

An airfoil includes an airfoil body that has a geometrically segmented coating section. The geometrically segmented coating section includes a wall having an outer side. The outer side has an array of cells, and there is a coating disposed in the array of cells.

A connecting assembly comprising an air distribution housing, between an air inlet passage and at least one duct connected with the housing by at least one bush mounted on an orifice of a wall of the housing. The wall of the housing and an inner wall of the bush are connected by a fillet having a radius which is maximum over an angular sector.

An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

A method for fabricating an airfoil for a gas turbine engine includes providing a core blank made of a cellular material, shaping the core blank into a cellular core, forming a fiber preform that has an airfoil section and a platform by laying-up first and second ceramic fiber ply skins on the cellular core such that in the platform the cellular core is sandwiched radially between the first and second ceramic fiber ply skins, the first and second ceramic fiber ply skins each include at least one 2-D ceramic fiber ply, and densifying the fiber preform with a ceramic matrix.

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.