The disclosure describes composite liners (such as acoustic panels, fan track liners, and/or ice impact panels or boxes for turbofan engines) and techniques for forming composite liners. In some examples, the composite liner includes at least one region comprising a reinforcement architecture comprising a matrix material, a plurality of relatively tough polymer-based reinforcement elements, and a plurality of second reinforcement elements. The plurality of relatively tough polymer-based reinforcement elements and the plurality of second reinforcement elements are embedded in the matrix material.

The invention relates to a blade (3) of a fan (1) of a turbomachine having a structure made of a composite material comprising a fibrous reinforcement (5) obtained by three-dimensional weaving and a matrix in which the fibrous reinforcement (5) is embedded, the fibrous reinforcement (5) comprising first strands (9) having a predetermined elongation at break, a portion of the fibrous reinforcement (5) further comprising second strands (10) having an elongation at break higher than that of the first strands (9).

The invention relates to a blade (3) of a fan (1) of a turbomachine having a structure made of a composite material comprising a fibrous reinforcement (5) obtained by three-dimensional weaving and a matrix in which the fibrous reinforcement (5) is embedded, the fibrous reinforcement (5) comprising first strands (9) having a predetermined elongation at break, a portion of the fibrous reinforcement (5) further comprising second strands (10) having an elongation at break higher than that of the first strands (9).

A preform charge is formed by forming an assemblage of preforms, wherein preforms in the assemblage are bonded to a neighboring preform such that the preform charge effectively becomes a single unit. The preform charge can then be added to a mold to fabricate a part via compression molding.

A manufacturing method of a halogen-free flame-retardant thermoplastic braided fiber reinforced polymer composite board, comprising steps of: preparing a recycled material containing a halogen-free flame-retardant thermoplastic braided fiber reinforced polymer composite; adding a polymer base material to the recycled material to form a core layer material and extruding the core layer material with a low shear extruder; hot pressing the core layer material by rollers to obtain a recycled fiber core layer; preparing a reinforcement layer containing a fiber material or a fabric with pores; and stacking and hot pressing the recycled fiber core layer and the reinforcement layer.

A method of manufacturing a fabric structure for use in manufacturing a composite aircraft blade. The method comprises: combining yarns including both reinforcing material filaments and a matrix material with yarns of reinforcing material filaments and/or yarns including at least one filament of matrix material; or by combining yarns of reinforcing material filaments with yarns including at least one filament of matrix material; or by combining yarns each comprising both reinforcing material filaments and matrix material. Combining may comprise weaving, knitting or braiding. The matrix material may be a thermoplastic.

A method of manufacturing a fabric structure for use in manufacturing a composite aircraft blade. The method comprises: combining yarns including both reinforcing material filaments and a matrix material with yarns of reinforcing material filaments and/or yarns including at least one filament of matrix material; or by combining yarns of reinforcing material filaments with yarns including at least one filament of matrix material; or by combining yarns each comprising both reinforcing material filaments and matrix material. Combining may comprise weaving, knitting or braiding. The matrix material may be a thermoplastic.

A reinforced composite laminate for an aircraft and a method of manufacture thereof. The laminate includes a set of stacked plies of pre-preg material laid up forming an XY plane, wherein the laminate further includes a plurality of elongated carbon pins including a round section with a diameter smaller than 0.5 mm. The pins are nailed through the stacked plies following the Z direction to withstand the out-of-plane loads.

A method for fabricating a composite part using a 3D printing machine. The method includes forming the part by depositing a plurality of part layers in a consecutive manner on top of each other where each layer is deposited by laying down rows of filaments made of a thermoplastic composite material. Reinforcing Z-pins are then inserted through the part layers to provide reinforcement of the part in the Z-direction. A plurality of additional part layers are deposited in a consecutive manner on top of each other on the part layers including the reinforcing Z-pins where each additional part layer is also deposited by laying down rows of filaments made of a thermoplastic composite material. Reinforcing Z-pins are also inserted through the additional part layers to provide reinforcement of the part in the Z-direction.

Some embodiments are directed to a three-dimensional (3D) preform including reinforcing fibres and shape memory alloys (SMA) wires and a composite material including a polymer matrix with a 3D-preform embedded therein, wherein the 3D-preform includes reinforcing fibres and shape memory alloy (SMA) wires.