A blade spar for a rotor blade for a rotor of an aircraft or vessel, preferably wherein the rotor is a propeller, the blade spar comprising a laminate structure. The laminate structure includes a plurality of plies of fibres in a matrix, wherein the blade spar has generally a longitudinal axis defining a longitudinal direction, the longitudinal axis extending along a radial direction of the rotor. The blade spar includes at least a portion that is curved from the longitudinal axis, wherein the plurality of plies comprises a first ply comprising a plurality of first fibres, wherein an alignment of the first fibres varies along the longitudinal direction to align the first fibres to the curved blade spar.

Application head for automated fiber placement, which application head includes at least: an application roller that is designed to apply fibers to a shaping tool which application roller is rotatably movable on its axis for applying fibers to the shaping tool, and a feed device includes a winding of a strip of fibers having a predefined orientation, the strip of fibers being configured to be transferred by unwinding from the feed device onto the application roller with at least one portion of the fibers of the strip being oriented such that they are not perpendicular to the axis of the roller.

Molding core for manufacturing an OMC hollow aeronautical part, in particular a fan module part, including a composite material including on the one hand a first phase of formula M.sub.n+1AlC.sub.n, where n=1 to 3, and M being a transition metal selected from the group consisting of titanium, niobium, chromium or zirconium, the composite material including on the other hand a second phase of formula Al.sub.4C.sub.3.

A device for moulding at least one bladed part of a turbomachine, including a base, a mould formed from several parts that are interlocked with each other. The mould is applied to the base and a first sealing device is mounted between the mould and the base. The bell-shaped dome is mounted on the mould and around the mould, the bell-shaped dome being applied to the base and a second sealing device being mounted between the bell-shaped dome and the base. The bell-shaped dome is configured to be held clamped against the base and includes inner surfaces cooperating by corner effect with complementary outer surfaces of the mould in order to apply a clamping force on the parts of this mould.

A method of repairing a wind turbine blade including a resin containing a cleavable functional group is provided, the method including applying an acidic aqueous liquid including an acid to a portion of a surface of the wind turbine blade, heating the portion of the surface of the wind turbine blade, applying a basic aqueous liquid including a base to the portion of the surface of the wind turbine blade. In addition, a repaired wind turbine blade obtainable by this method is also provided.

A device for moulding at least one bladed part of a turbine engine, including a base; a mould formed from a plurality of parts nested inside one another, this mould being applied to the base. A first seal is mounted between the mould and the base; and a bell is mounted on the mould and around the mould, this bell being applied to the base. A second seal is mounted between the bell and the base, this bell being configured to be held tight against the base and having interior surfaces engaging by wedge effect with complementary exterior surfaces of the mould in order to apply a clamping force on the parts of this mould.

A manufacturing method for a component made from composite material, in particular of a turbomachine, includes the steps of producing a preform with a fibrous reinforcement comprising a first fibrous portion and a second fibrous portion, and injecting a pressurized matrix into an injection chamber of an injection mold, in which the preform is arranged. The method further includes the steps of polymerizing the preform and positioning a flexible pocket that encloses a fluid and that is arranged between the first fibrous portion and the second fibrous portion before the injection step. The fluid is configured to apply an additional pressure to the preform of the fluid during the polymerization step.

A wind turbine blade is provided, including: a first and a second blade component connected with each other in an overlap region by thermal welding, a resistive element arranged between the first and second blade components in the overlap region as a remnant of the thermal welding, the resistive element having a first and a second terminal, a lightning conductor electrically connected with each of the first and second terminals, and a surge protection device, wherein one of the first and second terminals is electrically connected with the lightning conductor via the surge protection device. The resistive element which was used for the welding process and is left in the blade as a remnant of the welding process can be integrated into the lightning protection system of the blade.

A method for producing a blade includes providing a fibrous preform; providing a metal foil of elongate shape and including at least one indexing recess; and providing an injection mold having at least an upper part and a lower part. At least one of the upper part and the lower part includes at least one positioning projection. The method further includes the steps of arranging the fibrous preform in the injection mold; coating the leading edge of the fibrous preform with the metal foil, and inserting the positioning projection into the indexing recess so as to hold the metal foil in position on the leading edge. The method also further includes injecting a resin into the injection mold.