Abstract: The invention relates to a fan blade (3) made of composite material the fibrous reinforcement of which comprises first strands (12) having a first stiffness, second strands (13) having a second stiffness and third strands (14) having a third stiffness lower than the first stiffness and greater than the second stiffness, the blade comprising a first portion (15) comprising only first strands (12), a second portion (16) comprising only second strands (13) and a third portion (17) which is located between the first and second portions (15, 16) and which comprises both first, second and third strands (12, 13, 14); there is a gradual transition of properties at the interface between the different portions (15, 16, 17).

Abstract: Fan or propeller vane (1) for an aircraft turbomachine, the vane being made from a composite material and comprising a blade (2) and a base (3), the base being formed by a longitudinal end (41) of a spar (4) which is formed by a fibrous reinforcement formed from threads woven in three dimensions and a portion (42) of which extends inside the blade (2), the blade (2) having an aerodynamic profile which is defined by a skin (5) which is formed by woven threads and which surrounds the portion of the spar, the spar (4) and the skin (5) being embedded in a polymerised resin, characterised in that the portion (42) of the spar comprises projecting longitudinal stiffening members (6) which together delimit spaces (8) for receiving longitudinal inserts (7) which are formed from a honeycomb material.

Abstract: A method for automatically searching for at least one given textile pattern in a composite material reinforcement including a plurality of textile patterns, each textile pattern including a plurality of reinforcing yarns arranged according to a textile topology, the method including acquiring a three-dimensional image of the composite material reinforcement, and searching for the given textile pattern in the acquired three-dimensional image, using an artificial neural network trained on a training database to detect the given textile pattern in a three-dimensional image of a composite material reinforcement.

Abstract: The invention relates to a blade of a fan of a turbomachine, comprising a structure made from composite material, including a fibrous reinforcement obtained by means of the three-dimensional weaving of strands and a matrix in which the fibrous reinforcement is embedded,—the fibrous reinforcement comprising a first portion forming the leading edge and a second portion forming all or part of the trailing edge,—the strands of the fibrous reinforcement comprising first strands having a predetermined elongation at break and second strands having an elongation at break higher than that of the first strands, the first portion comprising all or some of the first strands while the second portion comprises all or some of the second strands.

Abstract: The invention relates to an inter-blade platform of a turbomachine fan, comprising: —a base comprising a first surface configured to delimit a flow path in the fan and a second surface on the opposite side from the first surface, —two flanks extending radially next to the second surface, each of the flanks having a sacrificial free end configured to bear against a fan disc.

Abstract: A fibrous texture forming the fibrous reinforcement of a turbomachine blade made of composite material which has a three-dimensional weaving between warp yarns or strands made of first fibers and weft yarns or strands made of first fibers, the texture including a blade root portion, a blade airfoil portion and a free end, the texture extending along the transverse direction between a first edge corresponding to a leading edge of the blade and a second edge corresponding to a trailing edge of the blade. The blade airfoil portion has a reinforced area extending along the longitudinal direction from the free end over a first length, and along the transverse direction from the second edge over a second length less, the reinforced area including weft yarns or strands made of second fibers different from the first fibers, the second fibers having an elongation at break greater than the first fibers.

Abstract: 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.

Abstract: A fibrous texture forming the fibrous reinforcement of a turbomachine blade made of composite material which has a three-dimensional weaving between warp yarns or strands made of first fibers and weft yarns or strands made of first fibers, the texture including a blade root portion, a blade airfoil portion and a free end, the texture extending along the transverse direction between a first edge corresponding to a leading edge of the blade and a second edge corresponding to a trailing edge of the blade. The blade airfoil portion has a reinforced area extending along the longitudinal direction from the free end over a first length, and along the transverse direction from the second edge over a second length less, the reinforced area including weft yarns or strands made of second fibers different from the first fibers, the second fibers having an elongation at break greater than the first fibers.

Abstract: Fan or propeller vane (1) for an aircraft turbomachine, the vane being made from a composite material and comprising a blade (2) and a base (3), the base being formed by a longitudinal end (41) of a spar (4) which is formed by a fibrous reinforcement formed from threads woven in three dimensions and a portion (42) of which extends inside the blade (2), the blade (2) having an aerodynamic profile which is defined by a skin (5) which is formed by woven threads and which surrounds the portion of the spar, the spar (4) and the skin (5) being embedded in a polymerised resin, characterised in that the portion (42) of the spar comprises projecting longitudinal stiffening members (6) which together delimit spaces (8) for receiving longitudinal inserts (7) which are formed from a honeycomb material.

Abstract: The invention relates to a blade of a fan of a turbomachine, comprising a structure made from composite material, including a fibrous reinforcement obtained by means of the three-dimensional weaving of strands and a matrix in which the fibrous reinforcement is embedded,—the fibrous reinforcement comprising a first portion forming the leading edge and a second portion forming all or part of the trailing edge,—the strands of the fibrous reinforcement comprising first strands having a predetermined elongation at break and second strands having an elongation at break higher than that of the first strands, the first portion comprising all or some of the first strands while the second portion comprises all or some of the second strands.

Abstract: The invention relates to an inter-blade platform of a turbomachine fan, comprising: —a base comprising a first surface configured to delimit a flow path in the fan and a second surface on the opposite side from the first surface, —two flanks extending radially next to the second surface, each of the flanks having a sacrificial free end configured to bear against a fan disc.

Abstract: A sealing arrangement is provided between inner and outer coaxial ring-shaped walls of an aircraft engine. The outer wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in a first direction. The inner wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in the opposite direction. The U-shaped end of the outer wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the inner wall. The U-shaped end of the inner wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the outer wall. The walls define therebetween a ring-shaped gas channel having a substantially S-shaped axial cross-section.

Abstract: A sealing arrangement is provided between inner and outer coaxial ring-shaped walls of an aircraft engine. The outer wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in a first direction. The inner wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in the opposite direction. The U-shaped end of the outer wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the inner wall. The U-shaped end of the inner wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the outer wall. The walls define therebetween a ring-shaped gas channel having a substantially S-shaped axial cross-section.