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 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.

A preformed material for use in fiber-reinforced composite materials, the preformed material including one or more fiber rovings including parallel fibers wherein the fiber rovings include one or more folds in a direction parallel to the direction of the fibers and wherein the unfolded width of the fiber rovings have a width included in a range from 0.3 mm to 5 mm. The fiber density by volume may be included in a range from 10% to 75% of fibers. The thickness of a fiber roving may be included in a range from 50 .Math.m to 2 mm. The fiber rovings may include from 500 to 12000 fibers. The fiber rovings may include a thermoplastic polymer that forms a first bond within the one or more folds and a second bond between a first fiber roving and a second adjacent fiber roving.

An object of the present invention is to obtain a fiber-reinforced composite material achieving both lightweight properties and mechanical properties at a high level. The present invention provides a fiber-reinforced composite material including a resin (A) and a reinforcing fiber (B), and having: a porous structure portion having micropores with an average pore diameter of 500 μm or less as measured by a mercury intrusion method; and a coarse cavity portion defined by the porous structure portion and having a maximum length of more than 500 μm as a cross-sectional opening portion.

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.

A fiber aggregation contains fiber containing a thermoplastic resin, each of the fiber being mutually joined and aligned.

A fiber aggregation contains fiber containing a thermoplastic resin, each of the fiber being mutually joined and aligned.

A reinforcing fiber composite material includes at least a matrix resin and discontinuous reinforcing fibers which include discontinuous reinforcing fiber aggregates, wherein the discontinuous reinforcing fibers include at least 5 wt % of discontinuous reinforcing fiber aggregates (A) in each of which a most widened section, where the width of the discontinuous reinforcing fiber aggregate in a direction intersecting the alignment direction of the discontinuous reinforcing fibers is made greatest when the discontinuous reinforcing fiber aggregate is two-dimensionally projected, is present at a position excluding both ends of the discontinuous reinforcing fiber aggregate, and the aspect ratio (width of the discontinuous reinforcing fiber aggregate/thickness of the discontinuous reinforcing fiber aggregate) of the most widened section is 1.3 times or more the aspect ratio of at least one of the ends of the discontinuous reinforcing fiber aggregate.

The invention relates to a flexible polymer composite containing metal particles, to the method for producing said composite, and to the uses of said composite.