Method for manufacturing a wind turbine blade comprising an aerodynamic shell forming an outer surface of the blade and at least one main laminate, the method comprising; providing a mould 13, forming a main laminate 18 in the mould by providing a fibre lay-up comprising a plurality of fibre plies placed on top of each other in the mould 13, dividing the fibre lay-up into at least two segments as seen in the longitudinal direction of the mould by at least one transverse flow barrier 54,55 in the lay-up preventing longitudinal resin flow through the fibre lay-up past the flow barrier 54,55.

A composite material includes a fibrous reinforcement and a polymer matrix. The polymer matrix includes two interpenetrating phases, namely a thermoset phase and a continuous thermoplastic phase. The thermoset phase and the thermoplastic phase form a matrix microstructure. The matrix microstructure includes a thermoplastic matrix formed by the thermoplastic phase. The matrix microstructure includes a multitude of thermoset particles formed by the thermoset phase. The thermoset particles have dimensions in a range between 0.1 m and 10 m.

The invention relates to a method for verifying the positioning of a fibrous preform in a blade, the blade having been obtained by injecting a resin into a mould having the shape of a blade and in which a preform has been placed, the blade extending in an orthonormal blade frame of reference X, Y, Z, the blade comprising a blade root extending longitudinally along an axis X, a vane extending from the blade root along an axis Z, the blade having a thickness defined along an axis Y, the preform comprising glass tracers positioned at the surface of the preform, the centre of the tracers defining a neutral axis located at a height along the axis Z in the direction defined by the axis X, the method comprising the following steps: the acquisition (E31) of tomographic 2D projections of the blade using an imaging system comprising an X-ray source, each projection being acquired at a given orientation of the X-ray source with respect to the blade; the combining (E32, E32a, E32b) of the 2D projections in the direction of the axis Y so as to obtain a cumulative 2D image in the directions X and Z; the determining (E33), for each pixel column defined in the direction of the axis Z, of a greyscale profile; the processing (E34) of each of the profiles obtained so as to locate the position, in Z, of the neutral axis in the direction of the axis X.

A method for manufacturing a part made of composite material for a turbomachine, in particular of an aircraft, includes the steps of: b) arranging a preform made of fibers in a mold, c) injecting polymerizable resin into the mold, d) machining the part, and e) visually checking the part. Step b) is preceded by a step a) in which at least one compliance coating is deposited in the mold. The compliance coating has a calibrated thickness (X) and at least one visual aspect identifiable by an operator. The coating is configured to cover at least one area of the preform and to be rigidly attached thereto by the resin at the end of step c). Step e) includes verifying, by the operator, the presence of the aspect in the area.

A method for producing a rotor blade of a wind turbine includes the following steps: a) providing at least two different components of the rotor blade, b) placing a resistive element between the components, c) placing a thermoplastic or weldable thermoset resin between the components, d) energizing the resistive element so that the resistive element applies heat to the thermoplastic or weldable thermoset resin to melt or to soften it, and e) joining the components together by means of the molten or softened thermoplastic or weldable thermoset resin.

A method for manufacturing an inter-blade platform of a turbomachine fan, the platform including a base including a first and a second sacrificial lateral edge having a thickness smaller than that of the central part of the base, the method including the production of a preform of the platform by three-dimensional weaving including a central part portion and two sacrificial edge portions, the thickness of which is smaller than that of the central part portion, the difference in thickness between the lateral edge portions and the central part portion being achieved by withdrawing a plurality of weft yarns located outside the central part portion and not being woven with warp yarns.

A propeller blade or airfoil of a turboprop of composite material includes a fibrous reinforcement densified by a matrix, the propeller blade or airfoil including, in a span direction, a root and an aerodynamic profile. The fibrous reinforcement includes a fibrous preform having a three-dimensional weave with a root preform portion present in the root and an aerodynamic preform portion present in the aerodynamic profile, the root and aerodynamic preform portions being linked to one another by the three-dimensional weave. The root preform portion of the fibrous preform includes an unlinked area delimiting an internal root recess forming a cavity opening at a free end of the root.

A process for manufacturing a blade made of composite material for a turbomachine is provided. The blade includes an airfoil having a pressure side and a suction side which extend from a leading edge to a trailing edge of the airfoil. The blade further includes a metal sheath that extends along the leading edge of the airfoil. The process includes the steps of: a) placing a preform, made by three-dimensionally weaving fibers, in a mold, a polymerizable adhesive being inserted between the sheath and the edge of the preform; and b) injecting polymerizable resin into the mold to impregnate the preform so as to form the airfoil after solidifying, wherein the resin is injected within a time interval during which the adhesive reaches a freezing point.

A web (12) is produced by hand layup, resin transfer moulding or vacuum infusion. The web (12) comprises a waved profile (17) defining a plurality of crest and valleys, the stitching yarns (32) thereof may optionally be aligned with the direction of the crests. The web (12) comprises one or more integrated projecting flanges (26) defining a bonding surface for connection with the spar caps (11) of the wind turbine blade (5). This web saves weight and reduces costs. There is also a wind turbine blade (5) and a manufacturing method.

A method of manufacturing composite blades comprises: laying up a pre-impregnated composite material to form a pre-impregnated composite structure; vacuum bagging the pre-impregnated composite structure between a first pressure plate and a second pressure plate; consolidating and curing the pre-impregnated composite structure to form a fiber-reinforced composite structure; and machining an overlap portion of the fiber-reinforced composite structure to form a first fiber-reinforced composite blade and a second fiber-reinforced composite blade.