A method of forming a wind turbine blade shear web flange section (36) by resin transfer moulding comprises providing a mould assembly (84) comprising a mould surface (86) defining a mould cavity and arranging a plurality of elongate flange elements (46) with the mould surface in an array (80) such that the flange elements are positioned one on top of another with first and second longitudinal ends (56,60) of each flange element longitudinally offset from respective first and second longitudinal ends of a neighbouring flange element so as to form a tapered portion (58,62) at each of a first and second longitudinal end of the flange section (36). A The method further comprises injecting resin to the mould cavity and curing the array of flange elements in a resin matrix to form a cured flange section having a laminate construction.

A method of manufacturing a tiltrotor wing structure including providing a spar mold having a plurality of bores extending from an exterior surface of the mold to an interior surface of the mold, the plurality of bores corresponding to a plurality of primary coordination holes in a spar member, the spar mold having a periphery defined by a top edge, a bottom edge and outboard ends; selecting a plurality of resin impregnated plies to ensure that the plies continuously extend beyond the periphery of the spar mold; laying the plies in the spar mold; curing the plies in the mold to form a cured spar member that extends beyond the periphery of the spar mold; and accurately drilling a plurality of primary coordination holes in the cured spar member in the spar mold using a tool positioned in the plurality of bores.

In one aspect, there is a joint member for a composite having a laminate layer including a support member having a first side and a second side; a first flange extending laterally from the first side and having an attachment surface for attachment to a structure; and a second flange extending laterally from the second side and having an attachment surface configured for attachment to the laminate layer. The joint member is configured to provide a load path from the first flange to the second flange. In an embodiment, a joint system for a composite system includes a joint member attached to a first skin and a second skin. In still another embodiment, a joint system for a rib assembly includes a joint member attached to a rib web and rib post.

In one aspect, there is an engagement member for splicing a spar assembly in an aircraft wing including a joining portion having a first attachment for connecting to a first spar and a second attachment surface for connecting to a second spar; and a rib post extending from the joining portion and disposed between the first attachment surface and the second attachment surface. In an embodiment, the rib post is integral to the joining portion and is configured to couple with a rib web.

A composite hat stringer for stiffening a panel includes a plurality of composite fabric plies arranged to form a cap, a pair of flanges and a pair of webs respectively connecting the cap with the pair of flanges. The cap includes at least one 0° composite tape ply interleafed in the composite fabric plies within the cap.

Methods for fabricating Class-A components (CAC) include providing a molding precursor which includes a first and second skin layer each including a fiber reinforcing material embedded in a polymer matrix, a third layer between the first and second skin layers and including a third polymer matrix and a filler material interspersed therein. The fiber reinforcing materials include a plurality of substantially aligned carbon fibers having a plurality of low strength regions staggered with respect to the second axis. The method includes disposing a molding precursor within a die, compression molding the molding precursor in the die, wherein the die includes a punch configured to contact the second skin layer, opening the die to create a gap between the punch and an outer surface of the second skin layer, and injecting a Class-A finish coat precursor into the gap to create a class-A surface layer and form the CAC.

The present invention relates to a wind turbine blade mould comprising a first mould part and a second mould part, where said first mould surface is configured for moulding a pressure side shell of a wind turbine blade, where said second mould surface is configured for moulding a suction side shell of a wind turbine blade, and where the wind turbine blade mould and thus also a wind turbine blade moulded in said mould comprise a first end, a second end, a pressure side shell, a suction side shell, and further comprise a leading edge area and a trailing edge area. The present invention also relates to a wind turbine blade and a manufacturing method for producing a wind turbine blade using a wind turbine mould as mentioned above.

A composite laminate for an airframe lifting surface including: at least two sides and one ramp area defined by a decreasing staggered laminate extended along a ramp direction, wherein the composite laminate includes: first plies formed by tapes arranged parallel to the ramp direction, second plies formed by tapes arranged orthogonal to the ramp direction, third plies formed by tapes arranged in a first laying up direction, being the first laying up direction different from the ramp direction and the direction orthogonal to the ramp direction, and fourth plies formed by tapes arranged in a second laying up direction, being the second laying up direction different from the ramp direction, the direction orthogonal to the ramp direction and the first laying up direction; wherein in the ramp area, the tapes forming the third and/or fourth plies are extended from one laminate side to another laminate side.

Provided is a cold press molded body having excellent fastening strength and fastening stability as well due to the use of a discontinuous carbon fiber and a discontinuous glass fiber for adjusting the volume, preferably the volume resistivity, of an end region (flowing region).

The present disclosure provides a lightweight spar cap with a concave structure for a wind turbine blade and a manufacturing method thereof, a wind turbine blade and a manufacturing method thereof. The lightweight spar cap is groove-shaped as a whole, and includes supporting portions located on two wings of the lightweight spar cap and an intermediate connecting portion connecting the two supporting portions. The manufacturing method of the lightweight spar cap includes laying a reinforcing body of the intermediate connecting portion and a supporting material of the supporting portion, and performing resin infusion. By comprehensively considering multiple factors, the present disclosure reduces the weight of the wind turbine blade, improves the material utilization of the wind turbine blade, and realizes a lightweight wind turbine blade.