A turbomachine blade that includes an airfoil that includes an intrados wall, an extrados wall, a leading edge, a trailing edge, an internal cavity and a plurality of cooling holes made in the walls and leading and trailing edges, each cooling hole connecting the internal cavity to the exterior, one end of each cooling hole opening up into the cavity, the other end of each cooling hole opening to the exterior through an outlet, wherein the cooling holes are distributed in at least one first alignment and a second alignment made in a wall of the airfoil, wherein this outlet of at least one of the cooling holes belonging to at least the second alignment is an oblong shape with its long dimension along the principal direction of said second alignment.

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.

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.

A gas turbine engine includes a fan and a core in flow communication with the fan. The core includes an aftmost turbine, and the aftmost turbine includes an aftmost stage of rotor blades. The gas turbine engine also includes a nacelle assembly having a translating and rotating thrust reverser system and enclosing the fan and at least a portion of the core. The nacelle assembly defines a nacelle assembly length between a forward lip and an aft edge. Additionally, the gas turbine engine defines an engine length between the forward lip of the nacelle assembly and the aftmost stage of rotor blades of the aftmost turbine. A ratio of the turbine length to the nacelle assembly length is greater than about 0.5 and less than about 1.

An exhaust system or nozzle for use in a gas turbine engine is disclosed herein. The exhaust system is adapted to adjust various streams of pressurized air produced by the gas turbine engine to control operation of the gas turbine engine.

An intermediate casing includes an inner wall having an outer surface extending along a longitudinal axis, the outer surface having a first profile in a first plane, an outer wall having an inner surface a second profile in the first plane, and first through fourth arms each extending radially. The outer and inner surfaces and the first and second arms delimit a first cavity, the first cavity having a first area and the outer and inner surfaces being separated by a first distance. The outer and inner surfaces and the third and fourth arms delimit a second cavity, the second cavity having a second area and the outer and inner surfaces being separated by a second distance. The first and second profiles are such that the first area is substantially identical to the second area and the first distance is different from the second distance.

A method for the manufacture of a component having an internal cavity is described. The method includes; defining an external geometry of the component, defining a core geometry of the component; using an additive layer manufacturing method, building the component from a plurality of layers laid on a first plane; wherein the core geometry includes a main core passage having a first end wall and a second end wall and is divided by one or more dividing walls, the dividing walls and end walls each having a common profile and wherein the profile includes an incline to the first plane.