A method for producing a hollow composite structure, such as a spar beam for a wind turbine blade, includes placing a membrane within a mold tool, the membrane being permeable to air and impermeable to resin. A mandrel is placed within the mold tool, the mandrel enclosed in an air tight layer that includes a vent. Fiber reinforcement material is placed around the mandrel within the mold tool and the membrane is sealed at least partly around the fiber reinforcement material and mandrel. The mold tool is closed with the vent line from the mandrel extending through the sealed membrane to outside of the mold tool. A vacuum is drawn in the mold tool while the mandrel is vented to outside of the mold tool, and while the vacuum is being drawn, resin is infused into the mold tool around the mandrel such that the resin is drawn towards the membrane.

A manufacturing method of a control surface of an aircraft, the control surface including an upper skin, a lower skin, ribs joining the upper skin and the lower skin and located along a chordwise direction of the control surface. The manufacturing method includes the steps of providing a single composite preform comprising the upper skin, the lower skin and the ribs, and curing the single composite preform such that an integrated box comprising the upper skin, the lower skin and the ribs is formed.

The invention relates to a wind turbine blade (1) comprising an outer casing formed at least in part of panels (3) of thermoplastic polymer composite, defining a leading edge (4) and a trailing edge (5) of the wind turbine blade, and at least one longitudinal stiffening member (6) made of polymer composite, extending along a longitudinal axis (A) of the wind turbine blade inside said wind turbine blade (1), said stiffening member (6) being arranged between at least one panel defining the leading edge (4) and at least one panel defining the trailing edge (5), characterized in that the thermoplastic polymer composite comprises a fibrous reinforcement and a (meth)acrylic thermoplastic polymer matrix and in that at least one panel (3) of thermoplastic polymer composite is connected to the stiffening member (6) by a weld-type interface (7).

A main laminate forming a load carrying structure for a wind turbine blade, the main laminate extending in a spanwise direction from a proximal end through a transition region to a distal end, wherein the main laminate comprises: a top side, a bottom side, and a thickness direction extending between the top side and the bottom side; a pultrusion portion including a bottom pultrusion element extending to a transition end of a transition portion located in the transition region of the main laminate; a plurality of stacked fibre-reinforced elements including bottom and top fibre-reinforced elements extending to a transition end of a transition portion located in the transition region,
wherein the pultrusion portion and the plurality of fibre-reinforced elements are connected by a joint in the transition region of the main laminate.

The present invention relates to an interlayer sheet for a spar cap comprising: a first fibre layer comprising a first plurality of fibres, having a first upper fibre surface and a first lower fibre surface, a second fibre layer comprising a second plurality of fibres, having a second upper fibre surface and a second lower fibre surface. The first fibre layer is arranged on top of the second fibre layer, such that the first lower fibre surface is in contact with the second upper fibre surface. The first fibre layer is of a different characteristic than the second fibre layer. Furthermore, the present invention relates to a spar cap for a wind turbine blade, comprising a plurality of pre-cured fibre-reinforced elements including at least a first pre-cured fibre-reinforced element and a second pre-cured fibre-reinforced element; and a number of interlayer sheets arranged between the plurality of pre-cured fibre-reinforced elements.

A composite platform for a fan of an aircraft turbine engine. The platform includes an elongate wall and is configured to extend between two fan blades. The wall includes an aerodynamic outer surface and an inner surface, on which a fastening tab is located, wherein the fastening tab is configured to be attached to a fan disc. The fastening tab is integrally formed with a metal reinforcement which has a plate having an elongate shape and which extends over more than 50% of the longitudinal extent of the wall, the wall being produced by overmolding a resin on the plate so as to be integrated into the wall.

Disclosed is a blade mould system for manufacturing of a wind turbine blade shell, the blade mould system comprising a blade mould having a moulding surface for defining an outer shape of a blade shell part, the blade shell part having an outer surface facing the moulding surface and an inner surface facing away from the moulding surface, and a first placement tool being positioned at a first placement tool position relative to the blade mould, the placement tool being adaptable between a first configuration and a second configuration. The first placement tool being configured to engage with a blade component being in a primary component position and position the blade component at a secondary component position relative to the moulding surface by the first placement tool attaining the second configuration, wherein the blade component is configured to be attached to the blade shell part in the secondary component position, wherein the first placement tool comprises a first movable part and a first stationary part.

A method for manufacturing of a pre-form part for a wind turbine blade including one or more components and an adhesive, wherein the component or at least one of the components is a mat-like component including fibres, includes the steps: arranging the adhesive at one or more positions on the component or arranging the components in a stack, wherein the adhesive is arranged at one or more positions between the components, and heating the adhesive by providing an electric current to at least one actively heated layer, wherein the mat-like component is used as actively heated layer and/or wherein at least one additional mat-like heating means provided and arranged on top of or below the component or the stack of components is used as actively heated layer.

The present disclosure relates to a spar cap (10) for a wind turbine blade (1000) comprising: a plurality of spar cap layers (20) and a first interlayer (30) arranged between the first spar cap layer (20a) and the second spar cap layer (20b) and comprising: a number of first interlayer areas (31), including a first primary interlayer area (31a), comprising a first number of interlayer sheets (33) comprising a first plurality of fibres (35); and a number of second interlayer areas (32), including a second primary interlayer area (32a), comprising a second number of interlayer sheets (34) comprising a second plurality of fibres (36), wherein the first number of interlayer sheets (33) is of a different characteristic than the second number of interlayer sheets (34).

The present embodiment relates to a composite fibre structure (100) and a method (200) of manufacturing the composite fibre structure (200). The composite fibre structure (100) includes a core (102) and an outer layer (108) enclosing the core (102). The core (102) further includes at least one of a permanent core (104) and a temporary core (106). The permanent core (104) is 3-D printed along with the temporary core (106) to form the core structure (102). The permanent core (104) and the temporary core (106) are placed alternatively along the section, extending throughout the length of the composite fibre structure (100), or the permanent core (104) and temporary core (102) can be alternate along the length of the composite fibre structure (100). The layer (108), made of a reinforcement material, wraps the core (102) to form the composite fibre structure (100).