The present invention relates to a method of manufacturing a wind turbine blade, comprising arranging one or more layers of fibre material and a preform in a mould (66), injecting the one or more layers of fibre material and the preform (76) with a curable resin, and curing the resin. The preform (76) is impregnated with a curing promoter such that the concentration of curing promoter varies spatially within the preform.

Provided are methods for heat curing of various materials, such as heat curable materials or more specifically potting compounds, which are disposed within cavities with limited access to these materials. Also provided are curing for executing such methods. In some embodiments, a heat curable material disposed within a cavity may be heated by a heating rod protruding into the cavity or through the cavity. The heating rod is thermally coupled to the heat curable material and is used to transfer heat to the heat curable material. For example, the heating rod may include a resistive heating element. The heating element may be positioned in such a way that the heat curable material is selectively heated within the cavity without significant heating of surrounding components. In some embodiments, the heating rod may be also used to compress the part containing the cavity or a stack including this part.

Provided are methods for heat curing of various materials, such as heat curable materials or more specifically potting compounds, which are disposed within cavities with limited access to these materials. Also provided are curing for executing such methods. In some embodiments, a heat curable material disposed within a cavity may be heated by a heating rod protruding into the cavity or through the cavity. The heating rod is thermally coupled to the heat curable material and is used to transfer heat to the heat curable material. For example, the heating rod may include a resistive heating element. The heating element may be positioned in such a way that the heat curable material is selectively heated within the cavity without significant heating of surrounding components. In some embodiments, the heating rod may be also used to compress the part containing the cavity or a stack including this part.

The present disclosure concerns a digital fabricating method for constructing 3D structures, comprising the following steps: (a) precursor consist of monomers and photo-initiator is introduced into reaction cell; (b) exposing the precursor to the DLP projector for several times to gain an inhomogeneous sheet; (c) swelling the sheet in solvent to gain 3D structure. The disclosure provides a simple and easy way to produce precise 3D structure.

Thermal curing of a potting material within a hole in a surface of a composite material is described utilizing a flexible vacuum compression device that includes a chemical-based heating pack. The vacuum compression device includes an internal compartment within a cavity that retains the chemical-based heating pack, and a vacuum port having a passage into the cavity. An end of the vacuum compression device includes an interface that forms an air-tight seal between the cavity and the surface when applied to a surface of the composite material. Drawing a vacuum via the vacuum port collapses the vacuum compression device and positions the chemical-based heating pack proximate to the surface, enabling heat from the chemical-based heating pack to thermally cure the potting material.

A part made of a fiber-reinforced composite material includes a structure made from a set of fibers supported in a thermosetting resin and a peel ply across all or part of the outer surface of the structure. The part has a gradient of polymerization at the interface between the structure and the peel ply. Also, methods for making such a part and methods for bonding such parts.

A method of forming an implant includes providing a preformed shell formed from at least one cured elastomeric layer. The shell includes an outer surface, an inner surface, and an opening for accessing an interior volume of the shell. The method further includes expanding the shell to an expanded state, in which the interior volume is greater than the interior volume of the shell at a time of forming the shell and forming an inner zone having at least one inner elastomeric layer on at least a portion of the inner surface of the shell, while the shell is in the expanded state, thereby forming a multi-zone shell. The method further includes reducing the interior volume of the multi-zone shell, thereby contracting the at least one inner elastomeric layer of the inner zone and causing texturing of the at least one inner elastomeric layer.

An efficient method for manufacturing a partially cured composite component intended to be joined with other component or components to form a composite structure and a manufacturing method of the composite structure. The partial curing of a composite layup is achieved using a mold comprising heat conductive elements and insulating elements and applying heat and pressure over the mold. The heat conductive elements are used to transmit or dissipate heat to/from the composite layup. The insulating elements are used to prevent the transmission or dissipation of heat to/from the composite layup.

A large area patterned film includes a first patterned area; a second patterned area; and a seam joining the first patterned area and the second patterned area, wherein the seam has a width less than about 20 micrometers. A method for tiling patterned areas includes depositing a predetermined thickness of a curable material; contacting a first portion of the curable material with a mold; curing the first portion of the curable material; removing the mold from the cured first portion of the curable material; contacting a second portion of the curable material with the mold, such that the mold contacts a portion of the cured first portion of the curable material; curing the second portion of the curable material; and removing the mold to yield a seam between the cured first portion of the curable material and the cured second portion of the curable material, wherein the seam has a dimension less than about 20 micrometers.

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.