A method for digitally designing a support with the shape of a fibrous blank obtained by three-dimensional weaving intended to form a fibrous preform of a turbine engine blade or propeller after shaping and compaction in a mold, includes providing a set of points representative of a face of the fibrous blank, the face being intended to form the root of the blade or the propeller and a portion of an aerodynamic profile of the blade or the propeller, generating a web connecting the points of the set of points, and digitally designing the support including at least an imprint of the fibrous blank having the shape of the generated web.

The invention concerns a method for producing a carbon fibre, that comprises a step of preparing a continuous fibre made of cellulose from cotton fabrics, by extracting, from these fabrics, cotton in the form of short, discontinuous fibres, and implementing a solvent spinning process; this step being followed by a step of carbonising said obtained continuous fibre made from cellulose, in order to form a carbon fibre. This carbon fibre can be used, in particular, for producing articles made from composite material made from carbon fibres and polymer organic resin.

The present invention relates to a method of molding a shell part of a wind turbine blade comprising the steps of providing a mold (64) comprising a mold cavity (66) with a root end (68) and an opposing tip end (70), arranging one or more preformed sheets (72a, 72b, 72c) in the mold cavity (66), wherein each preformed sheet comprises a mixture of fibre rovings (82) and a binding agent, wherein the fibre rovings are at least partially joined together by means of the binding agent, and injecting the one or more preformed sheets (72a, 72b, 72c) with a resin to mold the shell part. The present invention also relates to a shell part of a wind turbine blade obtainable by said method, to a preformed sheet for use in said method and to a method of manufacturing said preformed sheet.

The present invention relates to a method of molding a shell part of a wind turbine blade comprising the steps of providing a mold (64) comprising a mold cavity (66) with a root end (68) and an opposing tip end (70), arranging one or more preformed sheets (72a, 72b, 72c) in the mold cavity (66), wherein each preformed sheet comprises a mixture of fibre rovings (82) and a binding agent, wherein the fibre rovings are at least partially joined together by means of the binding agent, and injecting the one or more preformed sheets (72a, 72b, 72c) with a resin to mold the shell part. The present invention also relates to a shell part of a wind turbine blade obtainable by said method, to a preformed sheet for use in said method and to a method of manufacturing said preformed sheet.

The present invention relates to a blade (7) comprising: —a composite material structure (17), —a blade root fastening portion (9) further comprising a shoulder (10) extending into the recess from the wall—a base (18) arranged in the recess and comprising a support member configured to abut against the shoulder (10) of the blade root fastening portion (9) and a passage (39) formed in the support member, the sections (23) of the blade root portion (22) of the composite material structure extending through the passage (39), and—a blocking part (19) arranged in the recess between the two sections (23) of the blade root portion (22) such that each section of the blade root portion (23) is pressed against the support member by the blocking part (19).

Fan or propeller vane (1) for an aircraft turbomachine, the vane being made from a composite material and comprising a blade (2) and a base (3), the base being formed by a longitudinal end (41) of a spar (4) which is formed by a fibrous reinforcement formed from threads woven in three dimensions and a portion (42) of which extends inside the blade (2), the blade (2) having an aerodynamic profile which is defined by a skin (5) which is formed by woven threads and which surrounds the portion of the spar, the spar (4) and the skin (5) being embedded in a polymerised resin, characterised in that the portion (42) of the spar comprises projecting longitudinal stiffening members (6) which together delimit spaces (8) for receiving longitudinal inserts (7) which are formed from a honeycomb material.

Fan or propeller vane (1) for an aircraft turbomachine, the vane being made from a composite material and comprising a blade (2) and a base (3), the base being formed by a longitudinal end (41) of a spar (4) which is formed by a fibrous reinforcement formed from threads woven in three dimensions and a portion (42) of which extends inside the blade (2), the blade (2) having an aerodynamic profile which is defined by a skin (5) which is formed by woven threads and which surrounds the portion of the spar, the spar (4) and the skin (5) being embedded in a polymerised resin, characterised in that the portion (42) of the spar comprises projecting longitudinal stiffening members (6) which together delimit spaces (8) for receiving longitudinal inserts (7) which are formed from a honeycomb material.

The present invention relates to a process for impregnating a fibrous substrate consisting of long fibers by a liquid (meth)acrylic mixture mainly containing methacrylic and/or acrylic components. The invention also relates to such a (meth)acrylic mixture and its composition, said (meth)acrylic mixture comprising a (meth)acrylic syrup and an aqueous dispersion of radical initiator. The invention also relates to a process for manufacturing mechanical parts or structured elements or articles made of composite material by impregnating the fibrous substrate with the (meth)acrylic mixture then polymerizing said (meth)acrylic mixture, and also such parts obtained according to said manufacturing process and used in varied fields such as the automotive industry, aeronautics, or else construction.

The invention relates to a method (30) for producing a molded body (52) from a fiber material (50), wherein a textile structure (54) that is provided with a binder material is first produced from the fiber material (50) using a textile technology (step 32). This textile structure (54) is subsequently shaped (step 34) and fixed in a predetermined three-dimensional form by an activation of the binder material (step 36). The activation of the binder material (step 36) is carried out iteratively here. This means that the binder material is activated progressively in some selected areas of the textile structure (54) (and the shape of the structure is fixed in these areas as a result) before an activation/fixing is carried out in other areas of the textile structure (54).

A carbon fibre vehicle wheel including a wheel body having a rim portion and a face portion, the rim portion having an annulus structure configured to receive and seat a tyre. The face portion includes a hub configured to fix the wheel to the vehicle. A connection structure extends between and interconnects the hub and the rim. The wheel body has an inner side configured to face a wheel mount of the vehicle, and an outer side configured to face outwardly when connected to the wheel mount. The wheel body embodies a first carbon fibre composite composition including a carbon fibre layup infused with a first resin, and a fascia layer attached to at least a portion of the face portion of the outer side of the wheel body. The fascia layer embodies a second fibre composite composition including a selected fibre layup infused with a second resin.