Abstract: Turbojet engine fan module wheel, including a plurality of blades made of composite material, each blade having a root assembled with a base distinct from the bases of the other blades, each base having a groove extending axially and opening out on the side of the upstream face and on the side of the downstream face, each root cooperating by axial interlocking in a form-fitting manner, for example in the shape of a dovetail, with the groove of the base, whereby the root is retained on the base along the radial and circumferential directions, and each base cooperates with at least one part configured to axially block the root within the groove of the base, whereby the root is retained along the axial direction.

Abstract: A repair method for repairing an assembly including a main body and an old reinforcement, the assembly including an initial hole passing through the old reinforcement and at least a portion of the main body, the method including removing the old reinforcement; positioning a plug in the initial hole in the main body; fastening a new reinforcement on the main body, the new reinforcement covering the plug; and forming a new hole passing through the new reinforcement and at least a portion of the main body.

Abstract: A repair method for repairing an assembly including a main body and an old reinforcement, the assembly including an initial hole passing through the old reinforcement and at least a portion of the main body, the method including removing the old reinforcement; positioning a plug in the initial hole in the main body; fastening a new reinforcement on the main body, the new reinforcement covering the plug; and forming a new hole passing through the new reinforcement and at least a portion of the main body.

Abstract: A rotor of a turbomachine, such as a multi-flow turbojet engine fan, has a disc including, on the rim thereof, substantially axial slots with a dovetailed cross-section, and blades mounted individually in the slots, an axial wedge positioned between the root of the blades and the bottom of the slots, and a transverse lock providing upstream axial immobilization of the blades in the slot thereof. The lock is guided in radial notches formed in the flanks of the slots and radially supported against the wedge. The axial wedge is immobilised in the upstream direction, butting up against a transverse annular component secured to the disc.

Abstract: A rotor of a turbomachine, such as a multi-flow turbojet engine fan, has a disc including, on the rim thereof, substantially axial slots with a dovetailed cross-section, and blades mounted individually in the slots, an axial wedge positioned between the root of the blades and the bottom of the slots, and a transverse lock providing upstream axial immobilization of the blades in the slot thereof. The lock is guided in radial notches formed in the flanks of the slots and radially supported against the wedge. The axial wedge is immobilised in the upstream direction, butting up against a transverse annular component secured to the disc.