A blade for an aircraft gas turbine engine includes, in a longitudinal direction, a blade root, a shank and an aerofoil body, the aerofoil body extending in the longitudinal direction between the shank and a blade tip and in a transverse direction between a leading edge made of metal material and a trailing edge. The blade includes a blade core made of composite material having a three-dimensional woven fibrous reinforcement forming the blade root, the shank and a part of the aerofoil body. The blade also includes a skin made of composite material having a two-dimensional woven fibrous reinforcement surrounding the aerofoil body part of the blade core, the skin being interposed between the leading edge made of metal material and a front edge of the aerofoil body part of the blade core to define a thinned leading edge portion, the skin including one or more two-dimensional woven plies.

A fibrous texture has the shape of a strip extending in a longitudinal direction over a determined length between a proximal portion and a distal portion and in a lateral direction over a determined width between a first lateral edge and a second lateral edge. The fibrous texture has a three-dimensional or multi-layer weaving between a plurality of layers of warp strands extending in the longitudinal direction and a plurality of layers of weft strands extending in the lateral direction, the fibrous texture including first and second longitudinal sections extending over a width from the first or second lateral edge smaller than the determined width of the fibrous texture along the lateral direction. The first and second longitudinal sections each include warp strands and weft strands constituted by carbon fibers. The fibrous texture further includes a third section present between the first and second sections.

A method of manufacturing a composite guide vane with a metallic leading edge includes receiving a layup of fiber-reinforced composite sheets of continuous, substantially parallel and non-interlaced fibers impregnated with a resin. A vane body is formed from the layup of sheets. The vane body includes a body mid portion for interacting with a fluid and a body end portion. The method includes applying a metallic sheath on part of the vane body. The metallic sheath defines a leading edge of the guide vane. The method includes overmolding a head or a foot of the guide vane onto part of the vane body and onto part of the metallic sheath.

A method of fabricating a laminar composite article, includes steps of spreading a plurality of continuous fiber tows from a spool to form a first ply layer having a substantially consistent layer thickness, applying a binder to the spread plurality of continuous fiber tows, curing the plurality of continuous fiber tows and applied binder at a cure temperature less than a thermal decomposition temperature of the binder, and processing the cured plurality of continuous fiber tows at a post-cure temperature greater than the cure temperature.

A method for manufacturing a blade made of composite material for a turbine engine, in particular of an aircraft, the steps of injecting a resin in order to impregnate a fibrous preform woven in three dimensions and polymerizing the resin so as to form the blade that includes an airfoil, one longitudinal end of which is connected to a platform. The platform includes pressure and suction portions connected to the airfoil by a fillet, wherein a separation is formed in the fibrous preform between the pressure and suction portions. The method further includes reinforcing a leading edge of the airfoil; and reinforcing the fillets by integration of a metal reinforcement on at least one part of the pressure and suction portions of the platform and in the separation.

Provided is a vacuum pump in which the flexing of a rotating cylinder made of a fiber-reinforced resin can be reduced as much as possible to sufficiently reduce the gap between the rotating cylinder and a fixed cylinder, and exhaust performance can thereby be improved to great effect. A vacuum pump comprising a thread groove pump portion equipped with a fixed cylinder portion (2) having a spiraling thread groove portion (1) provided in an internal peripheral surface, and a rotating cylinder portion (3) placed inside the fixed cylinder portion (2), the thread groove pump portion exhausting through a spiraling exhaust flow channel due to the rotating cylinder portion (3) being caused to rotate, and the exhaust flow channel being formed from the thread groove portion (1) and an external peripheral surface of the rotating cylinder portion (3). The rotating cylinder portion (3) is configured by stacking a plurality of fiber-reinforced resin layers, and the outermost fiber-reinforced resin layer is thicker than the adjacent layer.

An assembly for a gas turbine engine according to an aspect of the present disclosure includes a metallic damper including a first contact surface and a gas turbine engine component. The gas turbine engine component includes a main body extending in a first direction between a gaspath surface and a second contact surface. The first and second contact surfaces oppose each other along an interface extending in a second direction. The first and second contact surfaces are dimensioned to contact each other along the interface in a hot assembly state. The main body is established by a composite including fibers in a matrix material. At least some of the fibers are arranged to establish a plurality of cooling passages aligned with the interface relative to the second direction. A method of damping for a gas turbine engine is also disclosed.

A method of fabricating a part out of composite material, includes forming a fiber texture from refractory fibers; placing the texture in a mold having an impregnation chamber including in its bottom portion a part made of porous material, the impregnation chamber being closed in its top portion by a deformable impermeable diaphragm separating the impregnation chamber from a compacting chamber; injecting a slip containing a powder of refractory particles into the impregnation chamber; injecting a compression fluid into the compacting chamber, to force the slip to pass through the texture; draining the liquid of the slip via the porous material part, while retaining the powder of refractory particles inside the texture so as to obtain a fiber preform filled with refractory particles; drying the fiber preform; unmolding the preform; and sintering the refractory particles present in the preform in order to form a refractory matrix in the preform.

A thrust reverser for a nacelle may comprise a composite track beam and a composite lug. The composite lug may be inserted through a through-hole in the composite track beam. Continuous fibers in the composite lug may provide strength in the in-plane direction.

Thrust reverser composite cascade (1), comprising at least one longitudinal wall (15) and transverse walls (14) connecting to this longitudinal wall, characterized in that the longitudinal wall comprises at least one continuous longitudinal fibre bundle (19) and the transverse walls each comprise at least one continuous transverse fibre bundle (23) crossing the longitudinal bundle, so that the intersections (16) of the transverse and longitudinal walls are structurally bridged in both directions by the reinforcing continuous longitudinal and transverse fibre bundles.