The present invention includes methods of preparing a composite structure comprising: placing a first ply of a fibrous material with a curable material on a layup tool; adding one or more additional plies on the first ply, wherein each of the one or more additional plies has a perimeter that is different in size around the perimeter than a previous ply to form a taper; and curing the composite structure, wherein the curable material is selected to minimize, limit, control, or eliminate the outflow of the curable material along the perimeter of the composite structure during the curing step.

Disclosed are a composite layer, a composite layer lamination and a method of manufacturing a composite layer. The composite layer includes: a resin core formed in a plate-shape and comprising with a plurality of guide protrusions protruding along an edge of the resin core as being spaced apart at a predetermined distance from each other and a plurality of guide notches between the plurality of guide protrusions; and a reinforcing fiber wound around the resin core via the plurality of guide notches functioning as a guide for the reinforcing fiber.

A composite panel assembly and method of forming the same includes a core, an inner skin coupled to a first side of the core, and an outer skin coupled to a second side of the core. A peripheral edge including portions of the core, the inner skin, and the outer skin, is compressed to close a path into the core.

Leaf spring comprising at least one leaf of composite material that comprises: a central body (1), and two eyes (2),
wherein the central body (1) comprises its longitudinal end zones (1.1) embedded in a cavity (2.1) of the eyes (2), wherein the sections transversal to the longitudinal direction of the central body (1) of the longitudinal end zones (1.1) of the central body (1) and the cavities (2.1) of the eyes (2) present increasing dimensions towards the longitudinal end of the leaf spring and that comprises fibre fabrics (7, 8, 9) of the central body (1) stacked in a Z-direction perpendicular to the longitudinal direction of the central body (1) and to the longitudinal direction of the hole (3) of the eyes (2) and comprises fibre fabrics (10, 11) of the eyes (2) stacked in a parallel direction to the longitudinal direction of the longitudinal axis of the hole (3).

The invention provides a wind turbine blade body manufacturing method, the method comprising the steps of: providing a mould (40) having an elongated mould surface (43), placing a movable insert (50) on the mould surface, in a first position, forming, with the insert in the first position, a first blade body having a first length (L1), placing the insert (50) on the mould surface, in a second position, and forming, with the insert in the second position, a second blade body having a second length (L2) which is different from the first length.

A method for manufacturing an outer skin of a rotor blade includes forming an outer skin layer of the outer skin from a first combination of at least one of one or more resins or fiber materials. The method also includes forming an inner skin layer of the outer skin from a second combination of at least one of one or more resins or fiber materials. More specifically, the first and second combinations are different. Further, the method includes arranging the outer and inner skin layers together in a stacked configuration. In addition, the method includes joining the outer and inner skin layers together to form the outer skin.

A composite prepreg laminate such as a hat type-stringer is formed on a contoured mandrel using a combination of mechanical sweeping and vacuum forming.

A wheel includes a rim having a rim well and rim flanges, a hub, and at least three spoke elements. Each spoke element forms at least one spoke between the hub and the rim. The spoke elements are fastened to an inside of the rim in a form-closed manner or a form-closed and bonded manner. In the hub region, the spoke elements are supported on each other in a circumferential direction at abutting surfaces designed therefor. A method for producing the wheel is provided.

A composite stiffener for a stiffener reinforced panel is disclosed. The stiffener has a longitudinal direction and a run-out region which terminates at an end of the stiffener. The stiffener also has a constant section region inboard of the run-out region in the longitudinal direction and having a constant cross section transverse to the longitudinal direction with a crown between adjacent foot portions. The run-out region has a changing cross section transverse to the longitudinal direction with a crown between adjacent foot portions and the crown reduces in height towards the end of the stiffener forming a ramp. The composite stiffener includes a number of blankets of non-crimp fabric layers.

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.