A bulk moulding compound comprising one or more cyanate ester, a catalyst, a filler and reinforcement fibres is provide, whereby the one or more cyanate ester is independently selected from a difunctional cyanate ester compound and/or a polyfunctional cyanate ester and mixtures of these cyanate esters. Furthermore, the catalyst is independently selected from the group consisting of 4,4′ methylene-bis(2,6-diethylaniline) (M-DEA), 4,4′-methylene-bis(3-chloro-2,6-diethyl¬aniline) (M-CDEA), aluminum(III)acetylacetonate, and mixtures thereof.

The present invention provides: a surface-coated film which is for being integrally formed with a fiber impregnation resin; a surface-coated fiber-reinforced resin molded product; and a manufacturing method thereof. The surface-coated film has a base film B and an easily adhesive layer A provided on the base film B, wherein the base film B has a flat layer b2 and an easily molded layer b1 adjacent to the easily adhesive layer A, the thickness of the easily adhesive layer A is 30-250 nm, the thickness of the base film B is 50-500 μm, the easily molded layer b1 and the flat layer b2 satisfy both expression 1 of 3≤ratio (EHb2/EHb1) of storage elastic modulus EHb2 of flat layer b2 at 150° C. to storage elastic modulus EHb1 of easily molded layer b1 at 150° C., and expression 2 of 1,000 MPa≤storage elastic modulus ELb1 of easily molded layer b1 at 23° C.

A method for manufacturing a wind turbine blade includes the use of an apparatus having an engagement part. The engagement part has: a support element having a first support edge and a second support edge, a belt extending around the support element and forming a primary engagement edge of the engagement part along the first support edge of the support element. The method includes: providing one or more pre-shaped elements, including a first pre-shaped element, in a first element position, positioning the engagement part in a first position, moving the support element in a first direction with a first velocity to extend underneath the first pre-shaped element, and at the same time moving the belt relative to the support element around the first support edge in a primary direction from below the first support edge to above the first support edge with a primary velocity.

The invention relates to an impregnation mould for manufacturing a turbine engine part, made of composite material, obtained from a preform made of a weave of fibres, said mould having first and second portions provided with respective recesses that define a cavity capable of receiving the preform, in which at least one injection means of the mould allows a resin to be injected in order to impregnate said preform, wherein said at least one injection means has a plurality of tubular injection needles, which are capable of extending from at least one of the first and second recesses to penetrate at least the weave of the preform in order to allow resin to be injected.

A method for manufacturing a blade made of composite material for a turbine engine, in particular of an aircraft, the steps of injecting a resin in order to impregnate a fibrous preform woven in three dimensions and polymerizing the resin so as to form the blade that includes an airfoil, one longitudinal end of which is connected to a platform. The platform includes pressure and suction portions connected to the airfoil by a fillet, wherein a separation is formed in the fibrous preform between the pressure and suction portions. The method further includes reinforcing a leading edge of the airfoil; and reinforcing the fillets by integration of a metal reinforcement on at least one part of the pressure and suction portions of the platform and in the separation.

A method of manufacture of a composite moulding material (1100) comprising a fibrous layer (1102) and a graphene/graphitic dispersion (1104) applied to the fibrous layer (1102) at one or more localised regions (1106) over a surface (1108) of the fibrous layer(1102) in which the graphene/graphitic dispersion (1104) is comprised of graphene nanoplates, graphene oxide nanoplates, reduced graphene oxide nanoplates, bilayer graphene nanoplates, bilayer graphene oxide nanoplates, bilayer reduced graphene oxide nanoplates, few-layer graphene nanoplates, few-layer graphene oxide nanoplates, few-layer reduced graphene oxide nanoplates, graphene/graphite nanoplates of 6 to 14 layers of carbon atoms, graphite flakes with nanoscale dimensions and 40 or less layers of carbon atoms, graphite flakes with nanoscale dimensions and 25 to 30 layers of carbon atoms, graphite flakes with nanoscale dimensions and 25 to 35 layers of carbon atoms, graphite flakes with nanoscale dimensions and 20 to 35 layers of carbon atoms, or graphite flakes with nanoscale dimensions and 20 to 40 layers of carbon atoms, in which the dispersion (1104) is applied to the fibrous layer (1102) using at least one valvejet print head (1112).

The invention relates to a thermoplastic composite material comprising a thermoplastic matrix and a fibrous material impregnated with the thermoplastic matrix, wherein the fibrous material comprises carbon fibers with a weight average aspect ratio of length divided by diameter (L/D) of at least 500; the thermoplastic matrix comprises a thermoplastic polymer and a laser absorbing additive.

A 3D printing machine includes a first spinning part moving in directions of three axes, i.e., X-, Y-, and Z-axes, to melt and spin a base material; and a second spinning part moving along a moving direction of the first spinning part to spin reinforcing fiber onto an upper surface of the spun base material, and moving clockwise or counterclockwise so that the reinforcing fiber is spun onto the upper surface of the base material at a moment when the first spinning part changes a moving direction thereof to the X- or Y-axis direction.

A fiber-reinforced shaped article in which a reinforcing fiber bundle aggregate formed of a plurality of reinforcing fiber bundles converged is impregnated with an epoxy resin composition and the epoxy resin composition is cured, wherein the epoxy resin composition contains at least components [A], [B], [C], and [D], and a quantity of [A] is 60 to 100 parts by mass per 100 parts by mass of all epoxy resin contained in the epoxy resin composition: [A]: aminophenol type epoxy resin; [B]: two kinds of acid anhydrides of [B1]: acid anhydride having a nadic anhydride structure, and [B2]: acid anhydride having a hydrogenated structure of phthalic anhydride; [C]: at least one filler having a Mohs hardness of 3 or less selected from the group consisting of a silicon compound, a magnesium compound, a calcium compound, an aluminum compound, and inorganic carbon; [D]: a release agent.

In a preferred embodiment, a composite panel with a smooth outer surface, ready for painting with or without addition of primer, may be created by constructing a panel layup assembly upon a mold, the panel layup assembly including a composite panel having a core and a resin formulation, and a release film between the mold and the composite panel, where a smooth release surface of the release film is in contact with the composite panel upon construction; initiating curing of the composite panel at a first temperature within a lowermost ten percent of a curing temperature range of the resin formulation; continuing curing of the composite panel at a second temperature above the lowermost ten percent of the curing temperature range; and completing curing of the composite panel at a third temperature below the second temperature.