The invention relates to a flexible polymer composite containing metal particles, to the method for producing said composite, and to the uses of said composite.

The invention provides a fitted platform (1) for positioning between two adjacent blades of an aviation turbine engine fan, said platform comprising a flow passage wall (10) made of composite material having a central portion (16) and first and second margins (18) each extending in a longitudinal direction of said wall, each margin extending over a determined distance (D) from the central portion (16) in a transverse direction of said wall, said flow passage wall comprising fiber reinforcement densified by a matrix, the platform being characterized in that the fiber reinforcement present in the central portion (16) presents three-dimensional weaving, and in that the fiber reinforcement present in the first and second margins (18) presents two-dimensional weaving, at least in part. The invention also provides a fan module, a turbine engine, and a method of fabricating such a platform.

The invention provides a fitted platform (1) for positioning between two adjacent blades of an aviation turbine engine fan, said platform comprising a flow passage wall (10) made of composite material having a central portion (16) and first and second margins (18) each extending in a longitudinal direction of said wall, each margin extending over a determined distance (D) from the central portion (16) in a transverse direction of said wall, said flow passage wall comprising fiber reinforcement densified by a matrix, the platform being characterized in that the fiber reinforcement present in the central portion (16) presents three-dimensional weaving, and in that the fiber reinforcement present in the first and second margins (18) presents two-dimensional weaving, at least in part. The invention also provides a fan module, a turbine engine, and a method of fabricating such a platform.

The invention relates to a method (30) for producing a molded body (52) from a fiber material (50), wherein a textile structure (54) that is provided with a binder material is first produced from the fiber material (50) using a textile technology (step 32). This textile structure (54) is subsequently shaped (step 34) and fixed in a predetermined three-dimensional form by an activation of the binder material (step 36). The activation of the binder material (step 36) is carried out iteratively here. This means that the binder material is activated progressively in some selected areas of the textile structure (54) (and the shape of the structure is fixed in these areas as a result) before an activation/fixing is carried out in other areas of the textile structure (54).

According to one embodiment, a system for manufacturing a fully impregnated thermoplastic prepreg includes a mechanism for moving a fabric or mat and a drying mechanism that removes residual moisture from at least one surface of the fabric or mat. The system also includes a resin application mechanism that applies a reactive resin to the fabric or mat and a press mechanism that presses the coated fabric or mat to ensure that the resin fully saturates the fabric or mat. The system further includes a curing oven through which the coated fabric or mat is moved to polymerize the resin and thereby form a thermoplastic polymer so that upon exiting the oven, the fabric or mat is fully impregnated with the thermoplastic polymer. During at least a portion of the process, humidity in the vicinity of the coated fabric or mat is maintained at substantially zero.

According to one embodiment, a system for manufacturing a fully impregnated thermoplastic prepreg includes a mechanism for moving a fabric or mat and a drying mechanism that removes residual moisture from at least one surface of the fabric or mat. The system also includes a resin application mechanism that applies a reactive resin to the fabric or mat and a press mechanism that presses the coated fabric or mat to ensure that the resin fully saturates the fabric or mat. The system further includes a curing oven through which the coated fabric or mat is moved to polymerize the resin and thereby form a thermoplastic polymer so that upon exiting the oven, the fabric or mat is fully impregnated with the thermoplastic polymer. During at least a portion of the process, humidity in the vicinity of the coated fabric or mat is maintained at substantially zero.

A method of fabricating a fiber structure by multilayer three-dimensional weaving between a plurality of weft yarns and of warp yarns, the fiber structure having at least first and second portions that are adjacent in the warp direction, the first portion presenting, in a direction perpendicular to the warp and weft directions, a thickness greater than the thickness of the second portion, includes making the first portion using a step of three-dimensionally weaving warp and weft layers in which a fiber fabric is formed in the form of a Mock-Leno weave grid in a core of the first portion together with skins at a surface of the first portion, a weave of the skins being modified locally so as to deflect certain warp yarns from said skins and weave them with the fiber fabric in the form of the Mock-Leno weave grid.

A gas turbine fan casing made of composite material with a fibrous reinforcement includes a plurality of superimposed turns of a strip-shaped fibrous texture having a three-dimensional weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns, the fibrous reinforcement being densified by a matrix. The fibrous texture includes at least one lateral section of variable thickness in which the weft yarns have a size or a count different from the size or the count of the weft yarns of the plurality of layers of weft yarns present in the remainder of the fibrous texture.

The invention relates to a method for producing a fibre composite body (2), in particular at least a part of a wheel, comprising the following steps: providing a mould (4) having at least one female mould part (6) and one male mould part, introducing a fibrous raw material (8) and a binder (10) into the female mould part (6), activating the binder (10) by an energy input (p, T) into the mould (4) to form a mould element (12) which is open to diffusion, joining together the mould element (12) which is open to diffusion and a preform structure (14), supplying a resin, so that the resin infiltrates at least partially into the mould element (12) which is open to diffusion and into the preform structure (14), and curing the resin, so that in this way the fibre composite body (2) is formed without a boundary layer.

Provided is a useful improvement in a CF-SMC manufacturing technique comprising an SMC manufacturing method using a continuous carbon fiber bundle having a filament number of NK and partially split into n sub-bundles in advance. In the SMC manufacturing method according to the present invention, a fragmentation processing using a fragmentation processing apparatus (A) below is performed on chopped carbon fiber bundles before being deposited on a carrier film. The fragmentation processing apparatus (A) comprises a first pin roller and a second pin roller, each of which has a rotation axis parallel to a rotation axis direction of the rotary cutter. The first pin roller is rotationally driven such that its pins move downward from above on its side facing the second pin roller, and the second pin roller is rotationally driven such that its pins move downward from above on its side facing the first pin roller.