A method and apparatus for the continuous fabrication of fiber-bundle-based and composite-tape based preforms and preform charges includes a mandrel about which a constituent material, which is maintained under tension, is wound. The tension is insufficient to fully consolidate the wound material.

Systems and techniques to provide a flexible, lightweight material that is also effective at protecting a body from ballistic threats are described. An example composite material described herein is fiber-based, and it includes one or more first regions where the fiber composite material is consolidated, and one or more second regions where the fiber composite material is unconsolidated. Example methods of manufacturing the composite material disclosed herein include using a specialized tool with a heated platen press or an autoclave. The tool may include one or more protrusions and/or cavities that contact a precursor composite material to transform the precursor material into a partially consolidated fiber composite material, which is suitable for use as body armor, among other potential applications for the manufactured composite material.

A method is provided for forming connections from reinforcing fibers between faces of a wall for a pressure container. The reinforcing fibers are gripped by tufting needles and are pushed through the faces, and loops are formed through which support elements are introduced. A corresponding method produces a pressure container.

The invention relates to a method for manufacturing a part made from composite material, having a body and one or more continuous fibre bundles in its interior, characterised in that it comprises the stages of: a) obtaining a body that includes one or more tubular cavities in its interior that extend between a first end, disposed on the outer surface of the body and which comprises an inlet orifice, and a second end, opposite to the first end; b) introducing resin in the liquid state and a continuous fibre bundle in the interior of at least one tubular cavity through its inlet orifice; and c) curing the resin until it solidifies, adhering to the body and fixing the continuous fibre bundle. The invention also relates to a system for manufacturing a part made from composite material and to the part made from composite material obtained.

The invention relates to a method for manufacturing a part made from composite material, having a body and one or more continuous fibre bundles in its interior, characterised in that it comprises the stages of: a) obtaining a body that includes one or more tubular cavities in its interior that extend between a first end, disposed on the outer surface of the body and which comprises an inlet orifice, and a second end, opposite to the first end; b) introducing resin in the liquid state and a continuous fibre bundle in the interior of at least one tubular cavity through its inlet orifice; and c) curing the resin until it solidifies, adhering to the body and fixing the continuous fibre bundle. The invention also relates to a system for manufacturing a part made from composite material and to the part made from composite material obtained.

A blade for an aircraft gas turbine engine includes, in a longitudinal direction, a blade root, a shank and an aerofoil body, the aerofoil body extending in the longitudinal direction between the shank and a blade tip and in a transverse direction between a leading edge made of metal material and a trailing edge. The blade includes a blade core made of composite material having a three-dimensional woven fibrous reinforcement forming the blade root, the shank and a part of the aerofoil body. The blade also includes a skin made of composite material having a two-dimensional woven fibrous reinforcement surrounding the aerofoil body part of the blade core, the skin being interposed between the leading edge made of metal material and a front edge of the aerofoil body part of the blade core to define a thinned leading edge portion, the skin including one or more two-dimensional woven plies.

A composite material blade molding method is for molding a composite material blade by curing a prepreg. The composite material blade has a back-side blade member and a belly-side blade member which are superposed and joined. The composite material blade molding method includes: a lamination step for forming a back-side laminate in a back-side molding die and forming a belly-side laminate in a belly-side molding die; an inner surface cowl plate disposition step for disposing an inner surface cowl plate for maintaining an inner space formed by the back-side laminate and the belly-side laminate; a die mating step for die-mating the back-side molding die and the belly-side molding die and disposing a foaming agent in the inner space maintained by the inner surface cowl plate; and a curing step for heating and expanding the foaming agent and heat-curing the back-side laminate and the belly-side laminate.

A composite filament for use in additive manufacturing such as fused filament fabrication is described along with methods of its construction and use. The composite filament includes a single continuous filament (e.g., a continuous carbon roving) and a polymer (e.g., a high glass transition polymer) in intimate contact. The composite filament is formed through immersion of the continuous filament in a solution of the polymer. The composite filament can be combined with an additional formation material in an additive manufacturing process.

A composite filament for use in additive manufacturing such as fused filament fabrication is described along with methods of its construction and use. The composite filament includes a single continuous filament (e.g., a continuous carbon roving) and a polymer (e.g., a high glass transition polymer) in intimate contact. The composite filament is formed through immersion of the continuous filament in a solution of the polymer. The composite filament can be combined with an additional formation material in an additive manufacturing process.

The present invention relates to a composite material comprising one or more fibre layers composed of a fibre material and an aromatic polycarbonate-based matrix material. The fibre layer(s) is/are embedded in the matrix material. The present invention further relates to a process for producing these fibre composite materials, to multilayer composite materials comprising several layers of fibre composite material, and to the use of the composite materials for production of components or housing components or housings, and to the components, housing components or housings themselves.