A method for producing a Spar Cap, trailing edge or other reinforced laminate structural part of wind turbine blade, the Spar Cap, trailing edge or other reinforced laminate structural part of wind turbine blade produced by the method and its use are provided. The method for producing a Spar Cap, trailing edge or other reinforced laminate structural part of wind turbine blade improves production efficiency and saves costs.

Described are various dual-tapered composite laminate structures. These structures may comprise a plurality of finite sub-laminate cards, each one of the plurality of cards having the same shape and size as the other ones of the plurality of cards and having opposing surfaces oriented in a card plane, opposing primary edges of the planar surfaces, and opposing secondary edges of the planar surfaces, the opposing secondary edges being perpendicular to the opposing primary edges. The finite sub-laminate cards are tacked relative to one another in a successively offset manner. Also described are methods of stacking and sliding (for offset) the finite sub-laminate cards. Tapered fuselage skin and fuel tank covers are also considered.

Compaction systems and methods of compacting components are provided. In one aspect, a laminate of a component can be laid up on a tool of a compaction system. The laminate defines a cavity. A noodle is positioned relative to or in the cavity. A noodle ring is then positioned relative to the noodle. For instance, the noodle ring can be placed over the noodle. A cross section of the noodle ring can be shaped complementary to a cross section of the noodle. A plunger of the compaction system is moved so that it engages the noodle ring. Particularly, the plunger is moved in such a way that a force is applied on the noodle ring so that the noodle ring compacts the noodle into the cavity.

A molding jig for molding a laminate, which includes reinforced fiber sheets laminated on each other, extends in the length direction, and has a cross-sectional shape having a curved portion in a cross section obtained by cutting the laminate on a plane orthogonal to the length direction, into a three-dimensional shape having a bent portion in the length direction. The molding jig includes a female die for forming the bent portion, a male die for engaging with the female die with the laminate therebetween for forming the bent portion, and a stretchable supporting member between the female die and the laminate. The laminate comes in contact with the male die on both length-direction sides of the molded bent portion, and the supporting member is over a region including the female-side molding surface.

A method and apparatus for a continuous compression molding machine. The continuous compression molding machine comprises a tooling die, extending through a heating zone and a cooling zone, a tooling sleeve, and a biasing system. The tooling sleeve corresponds to the tooling die and is for use in forming a thermoplastic composite part from a thermoplastic composite charge when the tooling sleeve with the thermoplastic composite charge is moved with respect to the tooling die through the heating zone and the cooling zone. The biasing system is configured to hold the thermoplastic charge at a first angle within the heating zone and hold the thermoplastic composite charge at a second angle within the cooling zone, as the tooling sleeve moves through the heating zone and the cooling zone with the thermoplastic composite charge. The first angle is different from the second angle.

Systems and methods are provided for fabricating a preform for a fuselage section of an aircraft. The method includes advancing a series of arcuate mandrel sections in a process direction through an assembly line, laying up fiber reinforced material onto the arcuate mandrel sections via layup stations, uniting the series of arcuate mandrel sections into a combined mandrel; and splicing the fiber reinforced material laid-up onto the arcuate mandrel sections.

A high modulus composite part is disclosed comprising a polymer resin; and a plurality of high-performance unidirectional glass fibers. The high-performance unidirectional glass fibers have an elastic modulus of at least 89 GPa and a tensile strength of at least 4,000 MPa, according to ASTM D2343-09. The composite part comprises a fiber weight fraction (FWF) of no more than 88% and an elastic modulus of at least 60 GPa, according to ASTM D7205.

A composite forming apparatus includes an end effector and a forming feature that is coupled to the end effector. The end effector moves the forming feature relative to a forming tool to form a composite ply over a forming surface of the forming tool or over previously formed composite material on the forming surface of the forming tool. The composite forming apparatus further includes a positioning member engaged with the forming feature. The engagement between the positioning member and the forming feature facilitates a position between the forming feature and the composite ply to promote uniform application of compaction force over the forming surface of the forming tool.

A method for forming a composite part includes positioning a composite ply over a forming surface of a forming tool, moving a forming feature into engagement with the composite ply to yield a formed ply, and, after the moving, securing the formed ply relative to the forming tool.

A composite forming apparatus includes an end effector, a forming feature that is coupled to the end effector, and a heating element that is coupled to the forming feature to heat the forming feature. The end effector moves the forming feature relative to a composite ply to form the composite ply over a forming tool or over a prior formed composite ply. The forming feature heats the composite ply via conduction.