A wind turbine blade shear web comprises an elongate panel (28) having a first side and an opposing second side and a longitudinally extending flange (30a, 30b) arranged along a longitudinal edge of the panel. The flange comprises a plurality of elongate flange sections (46) arranged along the first side of the panel and integrated therewith. Each flange section comprises a plurality of elongate flange elements arranged one on top of another and offset from one another in a longitudinal direction of the flange section (46) such that the offset between the flange elements defines a tapered portion at each of a first and second longitudinal end of the flange section. The tapered portions of longitudinally adjacent flange sections overlap to define at least one scarf joint between said adjacent flange sections.

A FRP tubular body includes a tubular fiber structure formed by winding a reinforced fiber sheet made of fabric. The reinforced fiber sheet includes first reinforced fiber bundles arranged such that a yarn main axis direction extends in a circumferential direction of the fiber structure and second reinforced fiber bundles arranged such that a yarn main axis direction extends in an axial direction of the fiber structure. The reinforced fiber sheet includes a starting end, a finishing end, and a general portion located between the starting end and the finishing end. The general portion includes the first reinforced fiber bundles and the second reinforced fiber bundles. At least one of the starting end or the finishing end is a decreased portion that is smaller than the general portion in an amount of reinforced fibers per unit length in the circumferential direction of the fiber structure.

A method of fabricating a composite assembly may include providing a first laminate and a second laminate respectively formed of first and second composite plies, and having a respective first and second cured section and a respective first and second uncured section. The method may further include interleaving the first composite plies in the first uncured section with the second composite plies in the second uncured section to form an interfacial region. The method may additionally include curing the interfacial region to join the first laminate to the second laminate and form a unitized composite assembly.

A large scale composite structure is fabricated by forming a plurality of composite laminate modules and joining the modules together along their edges using scarf joints.

A method for manufacturing a wind turbine blade, comprising the steps of: arranging (S2, S3) a joining portion (8) comprising a fibre lay-up inside adjacent blade sections, covering (S4) the joining portion (8) and the adjacent blade sections at least partially with a vacuum bag, and applying vacuum to a space (54) covered by the vacuum bag (19, 38), infusing at least the fibre lay-up (12, 13, 14, 15, 16, 17) with a resin (43) and curing (S5) the resin (43) to obtain a cured joining portion (44) joining the blade sections (20, 24) inside. A light-weight and at the same time strong blade section joint is provided. In particular, the strength of this laminate joint formed by vacuum infusion is comparable to the strength of the pristine laminate. Compared to a connection using an adhesive, the laminate joint formed by vacuum infusion provides a lighter and stronger blade section joint, in particular, a better weight-to-strength performance.

A method of manufacturing a wind turbine blade is described, the blade being formed from at least a pair of blade shells being joined together. For at least a portion of the wind turbine blade, the blade shells are joined by an overlamination applied between the edges of the blade shells, thereby substantially reducing or eliminating the need for a structural adhesive to join the blade shells, particularly in the area of the leading edge of the blade or the root region of the blade trailing edge. The overlamination can be formed from the same material as the blade shells themselves, thereby minimising the possibility of structural faults or cracks due to differences in materials or stiffness levels at the interface between the blade shells.

A method for manufacturing a thermoplastic composite product includes: providing a first and second thermoplastic composite component made from a consolidated stack of thermoplastic composite plies, said first and second component having a first and second ply drop off, respectively. The first and second components are positioned such that the first ply drop off and the second ply drop off are aligned, and the first and second components are fixedly connected by means of heating. The stacks of plies for the first and second components are constructed by stacking the plies in a stacking direction wherein the plies are arranged such that plies at a different position along the stacking direction are laterally offset relative to each other for the purpose of forming the first ply drop off and the second ply drop off, respectively, before consolidating.

Systems and methods are provided for fabricating composite parts. The method includes subdividing a laminate into zones, laying up tows of fiber reinforced material for the laminate over a layup mandrel via multiple laminations such that each lamination head applies tows in a different zone, and splicing the zones together to form the laminate during the laying up of the tows while moving the layup mandrel in a process direction during fabrication of the composite parts.

Systems and methods are provided for fabricating curved preforms of fiber reinforced material. Methods include laying up at least one ply onto a carrier of flexible material at a lamination station, loading the carrier onto a rail system, routing the carrier to a particular Ply-By-Ply (PBP) forming station at the rail system, separating the at least one ply from the carrier, and making the at least one ply into the preform via the particular PBP forming station.

Systems and methods are provided for fabricating a part on a mandrel. The system includes a series of stations divided into at least two groups of stations, wherein each group of stations performs fabrication operations on a particular zone of the mandrel.