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.

This invention relates to a wind turbine blade component, a method of manufacturing such a wind turbine blade component and a wind turbine blade comprising the wind turbine blade component. The wind turbine blade component comprising a stack of layers arranged in a first group and in a second group, wherein the layers of each group has the same width. The layers of each group is continuously offset in an edgewise direction to form a tapered edge profile. The first group of layers may be arranged relative to the second group, or in an alternating order. The layers of the first group may further have a first length which is greater than a second length of the layers of the second group.

A composite panel structure has opposing outer walls or surfaces and a core comprising a plurality of ribs extending between and connected to the outer walls and defining chambers which are filled with expanding foams, non-expanding foams, gases, or a combination thereof. The outer panel surfaces and internal chamber walls or ribs are made of woven or non-woven fibrous material impregnated with one or more resins. The panel structure may be used for making a variety of products including sports equipment such as sports paddles, surfboards, kite boards, skateboards, wakeboards, as well as construction panels for walls, ceilings or floors, display panels, panels for the vehicle industry, furniture, and other structures requiring high strength to weight properties.

According to one embodiment, a system for manufacturing a fully impregnated thermoplastic prepreg includes a mechanism for moving a fabric or mat and a drying mechanism that removes residual moisture from at least one surface of the fabric or mat. The system also includes a resin application mechanism that applies a reactive resin to the fabric or mat and a press mechanism that presses the coated fabric or mat to ensure that the resin fully saturates the fabric or mat. The system further includes a curing oven through which the coated fabric or mat is moved to polymerize the resin and thereby form a thermoplastic polymer so that upon exiting the oven, the fabric or mat is fully impregnated with the thermoplastic polymer. During at least a portion of the process, humidity in the vicinity of the coated fabric or mat is maintained at substantially zero.

A method for use in ply compaction in forming a composite structure. The method includes positioning a ply of material on a forming tool having a web surface and at least one flange surface extending from the web surface, positioning a chassis at a first location along a length dimension of the forming tool, selectively rotating a flange forming device, that is coupled to the chassis, about a yaw axis based on a relative orientation of the flange forming device to the at least one flange surface, applying, with the flange forming device, the ply of material onto the forming tool, moving the chassis relative to the forming tool to position the chassis at a second location along the length dimension of the forming tool, and repeating the selective rotation and the application steps at the second location.

A method for manufacturing a wind turbine blade, includes the steps of: arranging an upper mould including a pre-casted fibre lay-up on a lower mould comprising a dry fibre lay-up and a mould core, applying vacuum to a space between the upper and lower moulds and the mould core, infusing at least the dry fibre lay-up and a connection region between the dry fibre lay-up and the pre-casted fibre lay-up with a resin, and curing the resin.

By having the pre-casted fibre lay-up in the upper mould, the packing and positioning of dry composite materials on top of the mould core is avoided.

According to one implementation, a composite material molding jig 3 includes a tubular member 5 and at least one rigid plate member 6 (6A, 6B) so that a composite material structure O (O1, O2) having a hollow structure can be formed easily. The tubular member 5 has flexibility. The at least one rigid plate member 6 (6A, 6B) reinforces strength of the tubular member 5 partially. The tube is used in a state where air is introduced inside the tube. Further, according to one implementation, a composite material molding method includes using the above-mentioned composite material molding jig 3 in order to produce a composite material structure O (O1, O2) so that the composite material structure O (O1, O2) having a hollow structure can be formed easily.

A method manufactures a thermoplastic fiber-reinforced resin molded article by pressing one thermoplastic fiber-reinforced resin prepreg, a plurality of laminated prepregs, or a plurality of prepregs. The method includes: a step in which the temperatures of an upper die and a lower die are set to 170-270° C.; a step in which the prepreg is placed between the upper die and the lower die; a step in which a load is applied to the prepreg so as to deform the prepreg; a step in which the temperatures of the upper die and the lower die are lowered at a speed of 5 to 50° C. per minute; and a step in which, after the upper die and the lower die are sufficiently cooled, the upper die is raised and a thermoplastic fiber-reinforced resin molded article is extracted.

Methods, systems, and apparatuses are disclosed for the manufacture of composite components having incorporated reinforcing structures machined into composite material substrates, and composite components manufactured according to disclosed methods, and assemblies and larger structures comprising the composite material components.

An automated fiber bundle placement apparatus is configured to lay a strip-like fiber bundle impregnated with a thermoplastic resin on a stacking surface on an upper side of a placement die by moving a placement head and by emitting a laser from an emitting device to deposit the fiber bundle on the stacking surface incompletely. The emitting device is configured to emit the laser toward the fiber bundle laid on the stacking surface to its surface that is a reverse side of its surface facing the stacking surface.