A method for assembling blade parts of a wind turbine blade includes the steps of: obtaining information about a connection area of a blade part, at least one of selecting, customizing and manufacturing an adaptor piece depending on the obtained information about the connection area of the blade part, wherein the adaptor piece serves to connect the blade part with at least another blade part, and connecting the blade part to the adaptor piece. Independently manufactured blade parts of a wind turbine blade are assembled in a manner such that the assembled blade comes as close as possible to a single-casted blade.

Blower vane for an aircraft turbine engine, the vane comprising a blade connected to a root, the vane being made of a woven fibre-based composite material embedded in a polymeric resin, the vane further comprising a medium for identifying the vane, which is a radio-identification medium, the blower vane being characterised in that it comprises at least a first portion the fibres of which are only electrically conductive fibres, and at least a second portion the fibres of which are formed by a mixture of electrically conductive fibres and non-electrically conductive fibres, and in that the identification medium is located in or on the second portion.

In a first aspect of the invention there is provided a method of making a wind turbine blade. The method comprises providing a blade shell mould, providing a plurality of 5 substantially planar strips of reinforcing material, and arranging the plurality of strips in the mould in a first stack to form at least part of a first spar cap. The method further comprises providing a retaining clip having a substantially planar body and upper and lower flanges projecting transversely to the planar body, wherein the flanges and the body together define a first receiving region on a first side of the retaining clip, and the 10 method further comprises arranging the retaining clip on a side of the first stack such that the strips in the first stack are received in the first receiving region.

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 mandrel includes a generally elongated mandrel body comprising a resilient mandrel core and an elastomeric mandrel outer layer disposed outside the mandrel core. A method for fabricating a contoured stiffened composite panel is also disclosed.

An improved liner for a container in which gases, liquids, or powders are stored. The liner is a multi-layer structure made in a roto molding machine. The liner includes a first outer layer made of metallocene polyethylene, an intermediate gas and liquid impermeable layer, and one or more inner layers made of thermoplastic material compatible with the material stored inside the container. During the molding process, the three layers are made sequentially with the second and third layers being bonded and fused to the adjacent layer to form a uniform composite layer. The outer layer is made of metallocene polyethylene with superior rigidity and relatively low coefficient of thermal expansion making the liner less susceptible to cracking and useful as a layup structure for molding a structure around it. The liner is then used as a layup structure for outer fibers and infused resin.

According to a manufacturing method and device for manufacturing a composite material having reinforced base materials with a resin impregnated in the reinforced base materials. An unactivated powdered adhesive is applied to at least one surface of a plurality of carbon fiber sheets. The carbon fiber sheets are laminated to form a laminate. At least a portion of the unactivated powdered adhesive that is applied between layers of the laminate is removed using an airflow that flows from one exterior surface of the laminate to an opposite exterior surface of the laminate to form a preform having a first region in which the activated adhesive is impregnated in the laminate, and a second region in which a content density of the activated adhesive is less than that in the first region.

A construct for a hockey blade that includes a foam core. The foam core includes a first core face, a second core face, and a core edge. A first layer of resin preimpregnated tape is wrapped continuously around the first core face, the core edge and the second core face. A thread is stitched along the first layer of preimpregnated tape. A second layer of resin preimpregnated tape wrapped continuously around the first layer of resin preimpregnated tape.

The present invention is directed to a new concept for an internal metallic tank of large-scale high-pressure gasholder in which pluralities of internal tanks have been accumulated like a honeycomb structure and for the manufacturing processes of the internal metallic tank.

A core element is provided, having the shape of a block with a first surface, a second surface situated opposite the first surface, mutually facing longitudinal side faces, and mutually facing transverse side faces. The first surface is provided with the first groove that is a continuous groove which extends parallel to the longitudinal side faces. The longitudinal side faces are provided with the side wall grooves, the side wall grooves being continuous side wall grooves which extend between the first surface and the second surface and are separated from the first groove in the first surface.