A method of fabricating an airfoil fairing for a vane arc segment includes providing a mandrel that necks down through a mandrel neck portion, providing fiber plies around the mandrel to form a tube that defines at least a portion of an airfoil profile of an airfoil section of an airfoil fairing, the fiber plies following the mandrel neck portion such that the tube has a corresponding tube neck portion that necks down to a collar, and removing the mandrel from the tube.

A composite platform for an aircraft turbine engine fan includes a wall of elongate shape that is configured to extend between two fan blades. The wall has an aerodynamic external face and an internal face on which is disposed a fixing tab configured to be fixed to a fan disc. A method for manufacturing the composite platform includes the steps of: a) producing a preform by three-dimensionally weaving of fibers, b) unbinding some of the fibers of the preform to detach at least one longitudinal layer of fibers from the rest of the preform, c) inserting a metal reinforcement between this layer and the rest of the preform, and d) injecting a resin into the preform so as to form said wall and secure the reinforcement to this wall.

A seal includes a ceramic matrix composite ply having woven ceramic-based fibers in a ceramic-based matrix. The ceramic matrix composite ply has at least one bend formed about a bend axis and defines at least one rounded portion. A sealed assembly and a method of making a seal are also disclosed.

A process for manufacturing a blade made of composite material for a turbomachine. The blade includes an airfoil having a pressure side and a suction side which extend from a leading edge to a trailing edge of the airfoil. The blade further includes a metal sheath that extends along the leading edge of the airfoil. The process includes the steps of: placing a preform, produced by three-dimensionally weaving fibers, in a mold, the sheath being positioned on an edge of the preform intended to form the leading edge of the airfoil; and injecting polymerizable resin into the mold to impregnate the preform so as to form the airfoil after solidifying. At least one double-sided adhesive film may be inserted between the sheath and the edge of the preform prior to injection of the resin.

A vane for a turbine engine includes a body in the form of an aerodynamic profile formed by a shell produced from a composite material formed from a three-dimensional textile of reinforcement fibres consolidated by a hardened resin. The shell forms a pressure surface and a suction surface of the vane connected to each other while forming on one side a leading edge and on the opposite side a trailing edge of the vane, and a core including a core body surrounded by the shell. The core is produced from non-porous plastics material, and the core body is in the form of an aerodynamic profile and delimits at least one closed cavity of the core.

The present invention relates to a fan blade (3) having a structure made from a composite material, comprising a fibrous reinforcement (5), which is obtained by three-dimensional weaving of warp strands and weft strands, and a matrix in which the fibrous reinforcement (5) is embedded, wherein—the fibrous reinforcement (5) comprises a first portion (14) forming the trailing edge (9) of the structure made from a composite material and a second portion (15) forming its leading edge (8), and wherein—the warp strands of the fibrous reinforcement (5) comprise first strands (12) having a predetermined stiffness and second strands (13) having a greater stiffness than that of the first strands (12), the first portion (14) comprising all or part of the first strands (12) and being devoid of second strands (13) while the second portion (15) comprises all or part of the second strands (13).

A fibrous preform for forming the fibrous reinforcement of a composite material part, the fibrous preform being made as a single piece and obtained by three-dimensional weaving, the preform including first and second skins and a longitudinal stiffening portion connecting the first to the second skin, the longitudinal stiffening portion forming a stiffening element of the part in the longitudinal direction. The preform has an intermediate portion extending in the longitudinal direction between two end portions. The longitudinal stiffening portion includes, in the intermediate portion, longitudinal non-woven threads or strands held together by first transverse threads or strands coming from the first skin and second transverse threads or strands coming from the second skin. In the end portions, the longitudinal threads or strands of the longitudinal stiffening portion are woven with the transverse threads or strands.

Methods for producing an annular casing for an aircraft turbine engine are provided. The annular casing includes an annular body made from a composite material based on a first resin, and a fire-resistant outer layer which covers an external annular surface of the body and which is made from a composite material based on a self-extinguishing second resin. The method includes preparing a strip of a glass fabric preimpregnated with said second resin, this strip including woven fibres oriented in directions that are perpendicular to one another and inclined by an angle of approximately 45° with respect to the axis of elongation of the strip, and applying the strip to the external surface of the body so as to cover the entirety of this surface in a single pass of the strip around the body.

A method for repairing a part made of composite material includes producing a recessed section by removing the composite material at a damaged area, producing grooves extending on the two faces of the part from edges of the recessed section, producing orifices in the part opening out into the grooves, tree-dimensional weaving of a filling part fiber preforms including a central section having a shape corresponding to the shape of the recessed section and fiber bundles extending from the central section, placing the filling preforms respectively on either face of the part with the fiber bundles in the grooves on the faces of the part and in the orifices such that the fiber bundles open out into the grooves present on the opposite face of the part, impregnating the filling fiber preforms with a precursor resin of a matrix, transforming the resin into a matrix to obtain a filling part.

The invention relates to a composite blade (5) for a turbine engine rotor, for example, an unducted propeller, comprising a skin (6) made of woven fibres forming the outer profile of the blade and an attachment (11) with cylindrical geometry in the direction of the span emerging from the blade root (9), which attachment is intended to retain the blade (5) on a hub of the rotor, characterised in that it further comprises a spar (16) having a hollow tube structure made of braided carbon fibres, fixed to the attachment (11) and extending inside the skin (6) over at least part of the span of the blade (5). The invention also relates to a propeller comprising said blade and to a method for manufacturing said blade.