A method of manufacturing a blade component of rotor blade of a wind turbine includes providing a plurality of pultrusions constructed of one or more fibers or fiber bundles cured together via a resin material. The method also includes placing a protective cap over at least one end of one or more of the plurality of pultrusions. Further, the method includes heat treating a surface of the plurality of pultrusions while the protective cap remains over the at least one end. Moreover, the method includes removing the protective cap from the at least one end. The method further includes arranging the plurality of pultrusions in a mold of the blade component. In addition, the method includes infusing the plurality of pultrusions together so as to form the rotor blade component.

The invention provides a wind turbine blade body manufacturing method, the method comprising the steps of: providing a mould (40) having an elongated mould surface (43), placing a movable insert (50) on the mould surface, in a first position, forming, with the insert in the first position, a first blade body having a first length (L1), placing the insert (50) on the mould surface, in a second position, and forming, with the insert in the second position, a second blade body having a second length (L2) which is different from the first length.

Among other things, the present disclosure relates to a wind turbine rotor blade that can be assembled at the site of its wind turbine. The blade includes an internal structure which may be pre-fabricated with connections to the shell skin prior to being transported to the site of its wind turbine. A filler material may be injected into the layers of fabric making up the shell skin at the wind turbine site and allowed to harden at approximately atmospheric conditions.

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.

Provided is a vacuum assisted resin transfer molding method for producing a component, in particular a spar cap, of a rotor blade including a lightning protection system, wherein the vacuum assisted resin transfer molding method includes the steps of: a) placing) an electrically conductive beam fiber material of an electrically conductive beam, an electrically conductive fiber mat and an electrical conductor of the component in a mold arrangement electrically connecting the electrically conductive beam fiber material to the electrical conductor by means of the electrically conductive fiber mat, wherein an electrical connection between the electrical conductor and the electrically conductive fiber mat is generated, c) subjecting the mold arrangement to underpressure, d) applying an external pressure on the electrical connection from outside the mold arrangement, e) injecting resin into the underpressurized mold arrangement, and f) applying heat to the mold arrangement for curing the resin.

A manufacturing method of a turbomachine airfoil, such as an outlet guide vane airfoil, comprising positioning a first fibrous wall preform on a first mold portion, placing at least one core on the first wall preform, positioning a second fibrous wall preform on the core, assembling a second mold portion to the first mold portion so as to form a mold around the first and second wall preforms, applying a hardening treatment to the first and second wall preforms, removing the core, and positioning a reinforcing structure between the first wall preform and the second wall preform.

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.

There is disclosed a method of manufacturing a composite component comprising a main body and an integral flange, the method comprising applying fibre-reinforcement material on a tool having a main body portion and a flange-forming portion to provide a pre-form comprising a body region and a longitudinally adjacent flange region. The pre-form extends generally longitudinally between two longitudinal ends; and a trailing ply of the pre-form extends generally longitudinally between the longitudinal end closest to the flange region and an inner ply end located in the flange region or partway into the body region. Relative movement between the flange-forming portion and the main body portion causes sliding movement between the trailing ply and the flange-forming portion during a flange forming operation, thereby causing a tension force in at least the flange region of the pre-form of during forming of the flange.

A turbomachine blade includes a blading made of composite material with a fibrous reinforcement densified by a matrix and a metal leading edge formed by a metal foil, the foil having an intrados fin and an extrados fin which extend respectively over intrados and extrados faces of the blading by conforming to an airfoil of the blade, wherein the blade also includes at least one unidirectional fabric ply made of composite material on the leading edge between the blading and the metal foil, each unidirectional fabric ply extending at least partially over the intrados and extrados faces of the blading.

A fibrous preform of a turbomachine component has a three-dimensional weave formed by a plurality of woven strands, wherein, in a shear plane of the component, all or part of the strands present in this plane have fibers forming an angle between 10? and 50? with their centerline.