Abstract: A turbine engine blade made of composite material including fiber reinforcement densified by a matrix is fabricated by a method including: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for a blade root and an airfoil, at least one second portion forming a preform for a blade inner platform or for wipers of a blade outer platform, and at least one third portion forming a preform for reinforcing a blade inner platform or for overhangs of a blade outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade having fiber reinforcement constituted by the preform and densified by the matrix, and forming a single piece with an inner and/or outer platform incorporated therein.

Abstract: A method for fabricating turbine engine blade or vane made of composite material includes: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for at least a blade/vane airfoil, at least one second portion forming a preform for an inner part of a blade/vane inner platform or for an outer part of a blade/vane outer platform, and at least one third portion forming a preform for an outer part of a blade/vane inner platform or for an inner part of a blade/vane outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade, and forming a single piece with an inner and/or outer platform(s) incorporated therein.

Abstract: A turbomachine rotor wheel including blades made of composite material; an annular mounting plate; a plurality of composite material blades mounted on the mounting plate, each blade also including a top platform at its tip carrying radial labyrinth teeth; an orientation disk fastened coaxially around the mounting plate and including at its outer periphery a plurality of axial slots that are open at one end, each slot presenting a cross-section that matches the cross-section of a blade root so as to hold it angularly in position by co-operation of shapes; and a variable-diameter spring ring housed in part in an axial notch formed in each blade root and projecting axially relative thereto, the spring ring to come into radial abutment against an inside surface of the orientation disk during radial outward movement of the blades relative to the mounting plate.

Abstract: A method for fabricating turbine engine blade or vane made of composite material includes: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for at least a blade/vane airfoil, at least one second portion forming a preform for an inner part of a blade/vane inner platform or for an outer part of a blade/vane outer platform, and at least one third portion forming a preform for an outer part of a blade/vane inner platform or for an inner part of a blade/vane outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade, and forming a single piece with an inner and/or outer platform(s) incorporated therein.

Abstract: A turbine engine blade made of composite material including fiber reinforcement densified by a matrix is fabricated by a method including: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for a blade root and an airfoil, at least one second portion forming a preform for a blade inner platform or for wipers of a blade outer platform, and at least one third portion forming a preform for reinforcing a blade inner platform or for overhangs of a blade outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade having fiber reinforcement constituted by the preform and densified by the matrix, and forming a single piece with an inner and/or outer platform incorporated therein.

Abstract: A turbomachine rotor wheel including blades made of composite material; an annular mounting plate; a plurality of composite material blades mounted on the mounting plate, each blade also including a top platform at its tip carrying radial labyrinth teeth; an orientation disk fastened coaxially around the mounting plate and including at its outer periphery a plurality of axial slots that are open at one end, each slot presenting a cross-section that matches the cross-section of a blade root so as to hold it angularly in position by co-operation of shapes; and a variable-diameter spring ring housed in part in an axial notch formed in each blade root and projecting axially relative thereto, the spring ring to come into radial abutment against an inside surface of the orientation disk during radial outward movement of the blades relative to the mounting plate.

Abstract: A support arm (13) is intended to be installed in a radial position in an afterburner device of a bypass turbojet. The device comprises first and second inner annular casings defining a passage for a primary flow and an outer annular casing defining together with the first inner annular casing a passage for a secondary flow. The arm (13) comprises a monobloc structure made of composite material including two integral walls (14, 15), on the one hand, designed to define a groove (16) having a substantially V-shaped profile and, on the other hand, including first end parts (17) joined together and adapted to define a foot (18) and second end parts (19) adapted each to define at least one flange (20, 21) intended to be positively connected to the outer annular casing.

Abstract: A support arm (13) is intended to be installed in a radial position in an afterburner device of a bypass turbojet. The device comprises first and second inner annular casings defining a passage for a primary flow and an outer annular casing defining together with the first inner annular casing a passage for a secondary flow. The arm (13) comprises a monobloc structure made of composite material including two integral walls (14, 15), on the one hand, designed to define a groove (16) having a substantially V-shaped profile and, on the other hand, including first end parts (17) joined together and adapted to define a foot (18) and second end parts (19) adapted each to define at least one flange (20, 21) intended to be positively connected to the outer annular casing.

Abstract: The present invention relates to a method for bonding a first part (31) made of a composite to a second part (34), to a defined dimension (A), wherein an insert (32) is fitted onto said first part (31), said insert (32) protruding beyond said dimension (A), the insert (32) is machined until its surface is at said defined dimension, said second part (34) is placed on the insert (32) and the second part is fastened via the insert. The use of an insert makes it possible to produce, with high precision, a reproducible assembly, which can still be dismantled.

Abstract: A controlled hot flap shutter for a turbojet nozzle includes a friction surface made of metal, and including straight lateral flanks to reduce the gap between each controlled hot flap shutter and the tracking flap shutters adjacent thereto.

Abstract: A controlled hot flap shutter for a turbojet nozzle includes a friction surface made of metal, and including straight lateral flanks to reduce the gap between each controlled hot flap shutter and the tracking flap shutters adjacent thereto.

Abstract: A convergent turbojet exhaust nozzle comprising a ring of hinged flaps made up of controlled flaps and of follower flaps disposed in alternation and co-operating at their upstream ends with a peripheral sealing gasket arranged at the outlet from an afterburner channel, each flap being made out of a ceramic-matrix composite material, and at its upstream end, each flap being made integrally with bearing means for bearing against the above-mentioned peripheral gasket, and with spherical-joint means between their upstream ends.

Abstract: The invention proposes a long life nozzle flap for aircraft turbojets. This flap is remarkable in that it is composed of a hollow tapered body (10) flattened in the transverse direction along straight geometric generating lines (11), the body (10) forming a thin wall (12) with an approximately constant thickness E, this wall (12) comprising a continuous inner surface with a radius of curvature equal to at least 2×E, the wall (12) being made of a refractory composite material composed of reinforcing fibers (18) embedded in a matrix also made from a refractory material, the reinforcing fibers (18) being arranged in a plurality of continuous layers of fibers (18) stacked on each other, the fibers (18a) of a layer crossing the fibers (18b) of any adjacent layer.

Abstract: The invention proposes a long life nozzle flap for aircraft turbojets. This flap is remarkable in that it is composed of a hollow tapered body (10) flattened in the transverse direction along straight geometric generating lines (11), the body (10) forming a thin wall (12) with an approximately constant thickness E, this wall (12) comprising a continuous inner surface with a radius of curvature equal to at least 2×E, the wall (12) being made of a refractory composite material composed of reinforcing fibres (18) embedded in a matrix also made from a refractory material, the reinforcing fibres (18) being arranged in a plurality of continuous layers of fibres (18) stacked on each other, the fibres (18a) of a layer crossing the fibres (18b) of any adjacent layer.