Abstract: A preform for a turbine engine blade, the preform comprising a main fiber preform obtained by three-dimensional weaving and comprising a first longitudinal segment suitable for forming a blade root (21), a second longitudinal segment extending the first longitudinal segment upwards, and suitable for forming an airfoil portion (22), and a first transverse segment extending transversely from the junction between the first and second longitudinal segments, and suitable for forming a first platform (23), wherein the preform also includes at least one stiffener (40) fitted on the main fiber preform along at least a portion of the distal edge of the first transverse segment.

Abstract: A fiber preform for a turbine engine blade, the preform comprising a main fiber structure (40) obtained by a single piece of three-dimensional weaving, said main first structure (40) comprising a first longitudinal segment (41) suitable for forming a blade root, a second longitudinal segment (42) extending the first longitudinal segment (41) and suitable for forming an airfoil portion (22), and a first transverse segment (51) extending transversely from the junction (49) between the first and second longitudinal segments (41, 42) and suitable for forming a first tongue for a first platform, wherein the first transverse segment (51) extends axially over a length that is less than 30%, preferably less than 15%, of the length of the junction (49) between the first and second longitudinal segments (41, 42).

Abstract: A blade body made of composite material includes fiber reinforcement densified by a matrix, the blade body extending in a longitudinal direction between a root or bottom portion and a tip or top portion, and in a transverse direction between a leading edge and a trailing edge. The fiber reinforcement of the blade body includes a first portion constituted by a plurality of yarn layers interlinked by three-dimensional or multilayer weaving, and a second portion forming all or part of at least one leading edge or at least one trailing edge of a blade. The second portion includes a plurality of short fibers oriented in random manner, the yarns of the plurality of yarn layers of the first portion and the short fibers of the second portion being embedded in the matrix.

Abstract: A fairing ring for a bladed wheel is disclosed. The fairing ring includes an annular wall extending axially, the wall presenting a plurality of notches extending axially, each notch being configured to receive a leading edge or a trailing edge of a blade.

Abstract: A fan assembly for an aviation turbine engine, the assembly including a fan disk having at least one tooth and at least one platform mounted on the tooth of the fan disk, the platform including a box of composite material made from fiber reinforcement densified by a matrix, the box having a flow passage wall, a bottom wall, and two side walls extending radially between the bottom wall and the flow passage wall. The box of the platform includes an upstream opening at an upstream end of the platform and a downstream opening, and the assembly also includes a locking key housed in the box and passing through the upstream and downstream openings of the box, the locking key being blocked at each of its ends by a blocking element.

Abstract: A platform suitable for being interposed between two adjacent blades of a fan, and including a passage wall, a bottom wall, and axial and radial retention surfaces. The passage wall defines a fan air flow passage, the bottom wall presents a main surface for bearing against a fan disk, and the axial and radial retention surfaces are arranged at the two axial ends of the platform. The radial retention surface arranged at the upstream axial end of the platform is radially offset from the main surface of the bottom wall in the direction in which the bottom wall bears against the disk.

Abstract: Blade made of composite material, with an integrated platform, for an aircraft turbine engine, including a root connected to an aerofoil and having a connection platform between the root and the aerofoil, the root having a generally elongate shape along an axis (A) of elongation, the aerofoil having a curved cross-sectional shape and including a pressure face and a suction face, the platform including a first portion extending on the pressure-face side of the aerofoil and including a first longitudinal free edge and a second opposite longitudinal edge for connecting to the rest of the blade, the platform including a second portion extending on the suction-face side of the aerofoil and comprising a third longitudinal free edge and an opposite fourth longitudinal edge for connecting to the rest of the blade, wherein the first longitudinal free edge is concave and the third longitudinal free edge is convex, and, for any plane (P, P?) perpendicular to the axis of elongation and intersecting the platform, the dist

Abstract: A rotary assembly includes a fan disk including a tooth with an upstream face; a platform mounted on the tooth; and a shroud mounted at the upstream end of the disk. The platform, at its upstream end, includes a step with a radial portion that is extended by an axial portion to form a substantially L-shaped longitudinal section. The axial portion radially retains the platform against the tooth. The radial portion extends along the upstream face of the tooth and includes an opening for having a fastener element passing axially therethrough to mount the shroud on the disk. A face of the shroud includes an element that projects and passes through the opening and comes into contact with the upstream face. The element extends from the face of the shroud over a length that is longer than a thickness of the radial portion of the step of the platform.

Abstract: A rotary assembly of an aviation turbine engine, includes a fan disk having at least one tooth and at least one platform mounted on the tooth of the fan disk. The tooth of the fan disk includes a tab extending the tooth axially upstream, and the platform includes a locking ring at its upstream end for receiving the tab of the tooth of the fan disk. The assembly further includes a spacer positioned inside the locking ring so as to block the platform on the tab of the tooth of the fan disk.

Abstract: A preform for a turbine engine blade, the preform comprising a main fiber preform obtained by three-dimensional weaving and comprising a first longitudinal segment suitable for forming a blade root (21), a second longitudinal segment extending the first longitudinal segment upwards, and suitable for forming an airfoil portion (22), and a first transverse segment extending transversely from the junction between the first and second longitudinal segments, and suitable for forming a first platform (23), wherein the preform also includes at least one stiffener (40) fitted on the main fiber preform along at least a portion of the distal edge of the first transverse segment.

Abstract: A turbomachine rotary assembly includes a plurality of blades having roots positioned in the grooves of a rotor disk and an axial retention system of the blades. The axial retention system includes a removable lock mounted bearing against the upstream axial ends of two consecutive teeth of the disk so as to block the opening of the groove formed by the teeth. It includes removable parts suitable for being mounted at the upstream axial ends of the teeth and to block the lock by clamping the lock between the removable parts and the teeth once the lock is installed against the upstream axial ends of the teeth.

Abstract: A preform for a turbine engine blade, the preform being obtained by three-dimensional weaving and comprising a first longitudinal segment (31) suitable for forming at least a portion of a blade root, a second longitudinal segment (32) extending the first longitudinal segment (31) upwards, and suitable for forming at least a portion of a stilt portion, a third longitudinal segment (33) extending the second longitudinal segment (32) upwards, and suitable for forming an airfoil portion, a first transverse segment (34) extending transversely from the junction between the second and third longitudinal segments (32, 33), and suitable for forming a first platform, and a first oblique segment (36) extending from the junction between the first and second longitudinal segments (31, 32) to the first transverse segment (34), and suitable for forming a retaining leg (26) for the first platform.

Abstract: A fiber preform for a turbine engine blade and also a single-piece blade suitable for being formed using such a preform, a rotor wheel, and a turbine engine including such a blade, the fiber preform being obtained by three-dimensional weaving and comprising a first longitudinal segment suitable for forming a blade root (21), a second longitudinal segment extending the first longitudinal segment upwards and suitable for forming an airfoil portion (22), a first transverse segment extending transversely from the junction between the first and second longitudinal segments and suitable for forming a first platform (23), and a first stiffener strip extending downwards from the distal edge of the first transverse portion and suitable for forming a first platform stiffener (25).

Abstract: A fan assembly for an aviation turbine engine, the assembly including a fan disk having at least one tooth and at least one platform mounted on the tooth of the fan disk, the platform including a box of composite material made from fiber reinforcement densified by a matrix, the box having a flow passage wall, a bottom wall, and two side walls extending radially between the bottom wall and the flow passage wall. The box of the platform includes an upstream opening at an upstream end of the platform and a downstream opening, and the assembly also includes a locking key housed in the box and passing through the upstream and downstream openings of the box, the locking key being blocked at each of its ends by a blocking element.

Abstract: A preform for a turbine engine blade, comprising a main fiber preform obtained by three-dimensional weaving and comprising: a first longitudinal segment, suitable for forming a blade root; a second longitudinal segment, extending upwards from the first longitudinal segment and suitable for forming an airfoil portion; and a first transverse segment, extending transversely from the junction between the first and second longitudinal segments to a substantially linear distal edge and suitable for forming a first platform; the preform further including at least one attachment tab provided under the first transverse segment at its distal edge, suitable for forming an attachment portion of the platform.

Abstract: A rotary assembly includes a fan disk including a tooth with an upstream face; a platform mounted on the tooth; and a shroud mounted at the upstream end of the disk. The platform, at its upstream end, includes a step with a radial portion that is extended by an axial portion to form a substantially L-shaped longitudinal section. The axial portion radially retains the platform against the tooth. The radial portion extends along the upstream face of the tooth and includes an opening for having a fastener element passing axially therethrough to mount the shroud on the disk. A face of the shroud includes an element that projects and passes through the opening and comes into contact with the upstream face. The element extends from the face of the shroud over a length that is longer than a thickness of the radial portion of the step of the platform.