Abstract: The invention relates to a fan blade (1) comprising: —an aerofoil (8) made of a composite material comprising a fibrous reinforcement densified by a polymer matrix, a leading edge (4) and a trailing edge (5), and —a structural shield (10) fitted and attached to the leading edge (4) or the training edge (5), and —at least one stiffener (20) formed integrally and in one piece with the structural shield (10), said stiffener (20) extending in a cavity (15) formed between the shield (10) and the leading edge (4) or the trailing edge (5) so as to increase a stiffness of the blade (1).

Abstract: A discharge duct (30) of an intermediate housing hub for an aircraft turbojet engine, comprises an inlet end (41) and an outlet end (42), intended to ensure the passage of air from at least one discharge inlet opening to at least one secondary outlet opening, and comprising an ejection grill (32) arranged at the outlet end (42), the ejection grill (32) comprising a plurality of fins (43), characterised in that the fins (43) comprise flow channels (44) for a fluid to be cooled, so as to form a heat exchange system.

Abstract: The invention relates to a fan blade (1) comprising: —an aerofoil (8) made of a composite material comprising a fibrous reinforcement densified by a polymer matrix, a leading edge (4) and a trailing edge (5), and —a structural shield (10) fitted and attached to the leading edge (4) or the training edge (5), and —at least one stiffener (20) formed integrally and in one piece with the structural shield (10), said stiffener (20) extending in a cavity (15) formed between the shield (10) and the leading edge (4) or the trailing edge (5) so as to increase a stiffness of the blade (1).

Abstract: The invention relates to an assembly of turbine engine (50) parts having a longitudinal axis (X), the assembly comprising at least two adjacent fan blades made of a 3D woven composite material, each blade (1) comprising a root (3), a vane (2) extending from the root (3), and an integrated platform (4) inserted between the root (3) and the vane (2), the platform (4) extending on either side of the vane (2) and forming a pressure face platform portion (4I) and a suction face platform portion (4E), the pressure face and suction face platform portions of adjacent blades being connected by a fin (14) extending at least radially at the outer side of the pressure face and suction face platform portions (4I, 4E), relative to the longitudinal axis (X), having a substantially triangular transverse cross section and extending axially and so as to upper overlap the longitudinal edges (11A, 11B) of the pressure face and suction face platform portions (4I, 4E) of the adjacent blades.

Abstract: A stator vane including a vane root, a vane tip, a leading edge extending between the root and the tip, the leading edge having a serrated profile having a succession of teeth and of troughs each having an amplitude and a thickness, wherein a series of at least three teeth and three consecutive troughs starting from the vane root and/or from the vane tip have a growing amplitude and/or thickness.

Abstract: An assembly for a primary flow path of a double flow turbomachine extending along a longitudinal axis including a reduction gear, configured to drive a fan in rotation, a stator including a plurality of vanes for straightening the primary flow path, and an intermediate casing, positioned downstream of the stator, including structural arms with fairings passing through the primary flow path, wherein a fairing and one straightening vane are connected together within the primary flow path by a connecting surface, the fairing and the vane being positioned longitudinally substantially at the reduction gear.

Abstract: A discharge duct (30) of an intermediate housing hub for an aircraft turbojet engine, comprises an inlet end (41) and an outlet end (42), intended to ensure the passage of air from at least one discharge inlet opening to at least one secondary outlet opening, and comprising an ejection grill (32) arranged at the outlet end (42), the ejection grill (32) comprising a plurality of fins (43), characterised in that the fins (43) comprise flow channels (44) for a fluid to be cooled, so as to form a heat exchange system.

Abstract: An assembly for a turbine engine or turbine engine test bed, including a hub defined about a longitudinal axis, a blade, including a blade root, extending in a radial direction to the longitudinal axis, the hub including a recess capable of receiving the blade root by insertion in the radial direction, wherein the recess includes a groove, the blade root including a groove, so that the two grooves are facing each other when the blade root is inserted into the recess, the assembly further includes a seal located in the two grooves.

Abstract: An assembly for a primary flow path of a double flow turbomachine extending along a longitudinal axis including a reduction gear, configured to drive a fan in rotation, a stator including a plurality of vanes for straightening the primary flow path, and an intermediate casing, positioned downstream of the stator, including structural arms with fairings passing through the primary flow path, wherein a fairing and one straightening vane are connected together within the primary flow path by a connecting surface, the fairing and the vane being positioned longitudinally substantially at the reduction gear.

Abstract: A stator vane including a vane root, a vane tip, a leading edge extending between the root and the tip, the leading edge having a serrated profile having a succession of teeth and of troughs each having an amplitude and a thickness, wherein a series of at least three teeth and three consecutive troughs starting from the vane root and/or from the vane tip have a growing amplitude and/or thickness.

Abstract: An assembly for a turbine engine or turbine engine test bed, including a hub defined about a longitudinal axis, a blade, including a blade root, extending in a radial direction to the longitudinal axis, the hub including a recess capable of receiving the blade root by insertion in the radial direction, wherein the recess includes a groove, the blade root including a groove, so that the two grooves are facing each other when the blade root is inserted into the recess, the assembly further includes a seal located in the two grooves.

Abstract: The invention relates to an assembly of turbine engine (50) parts having a longitudinal axis (X), the assembly comprising at least two adjacent fan blades made of a 3D woven composite material, each blade (1) comprising a root (3), a vane (2) extending from the root (3), and an integrated platform (4) inserted between the root (3) and the vane (2), the platform (4) extending on either side of the vane (2) and forming a pressure face platform portion (4I) and a suction face platform portion (4E), the pressure face and suction face platform portions of adjacent blades being connected by a fin (14) extending at least radially at the outer side of the pressure face and suction face platform portions (4I, 4E), relative to the longitudinal axis (X), having a substantially triangular transverse cross section and extending axially and so as to upper overlap the longitudinal edges (11A, 11B) of the pressure face and suction face platform portions (4I, 4E) of the adjacent blades.