Components are fastened with inserts that are placed into a hole in the component and bonded with an adhesive. A decoupling element is provided on the front face of the insert. This diverts the forces around the highly stressed front face of the inserts. The insert may be of a material with a lower stiffness compared with the adhesive. This arrangement may reduce stress peaks and increase the load capacity of the connection. A tool may be provided that reduces air inclusion between the insert and the component during fitting. The connection arrangement can be used when components of different stiffnesses have to be securely connected to one another. This applies to, among other things, fastening of fibre composite components or mineral components to metal components.

An adhesive injection method is for injecting an adhesive that bonds an outer plate and a reinforcing member. The reinforcing member has through holes bored through the reinforcing member in a direction intersecting a bonding surface facing the outer plate. The method includes positioning the outer plate and the reinforcing member; disposing a sealing material covering a gap between the outer plate and the reinforcing member; and injecting the adhesive into the through holes in order from one end to the other end of the bonding surface. At the injecting, while the adhesive is injected into the through hole, when the adhesive is recognized through another through hole formed adjacent to the through hole into which the adhesive is being injected, a through hole into which the adhesive is to be injected is shifted from the through hole into which the adhesive is being injected to the other through hole.

A method of fastening a joining insert to a wind turbine rotor blade element, the method including: providing a wind turbine rotor blade element of a fiber-reinforced composite material, the rotor blade element having a joining surface and a blind hole, the blind hole having a proximal end at the joining surface and a distal end within the fiber-reinforced composite material; forming a channel through the fiber-reinforced composite material, the channel connecting the distal end of the blind hole to a channel opening at an inner and/or outer surface of the rotor blade element; placing a joining insert in the blind hole; filling a space between the joining insert and the blind hole with a liquid plastics material in a vacuum infusion process, wherein the channel opening is connected either to a liquid plastics material supply line or to a process suction line; curing the liquid plastics material.

An example method of joining a first structure and a second structure is described that includes forming a bond cavity between a first structure and a second structure, placing a semi-permeable breather material at one or more exits of the bond cavity, placing a vacuum bag around the bond cavity and the semi-permeable breather material, evacuating the bond cavity via a vacuum port and forcing adhesive into the bond cavity via an adhesive port while the bond cavity is evacuated, and curing the adhesive via one or more heaters to bond the first structure to the second structure.

A method for forming thermoplastic composites includes: (a). cutting a thermoplastic film and a cloth material, with the thermoplastic film including a surface layer and an adhesive layer, and with a melting point of the surface layer higher than the adhesive layer; (b). placing the thermoplastic film on a platform of a molding machine, facing the adhesive layer upwardly, and covering the cloth material on the thermoplastic film, with the platform including a plurality of channels defined therein, a plurality of concave and convex patterns arranged on a top surface thereof, and plural pores evenly formed on the top surface thereof and communicating with the plurality of channels; and (c). heating the thermoplastic film by using a heating unit to melt the adhesive layer and to soften the surface layer.

The present invention relates to a method of manufacturing a wind turbine blade having a first member with a first joining surface and a second member with a second joining surface. The method includes applying at least one resin barrier to one or both of the joining surfaces, and subsequently locating the first and the second members adjacent each other so that they are joined by the at least one resin barrier. Hereby at least one cavity is formed between the first and second joining surfaces, which cavity is delimited by the at least one resin barrier. Subsequently resin is filled into the at least one cavity, and the resin is cured. The first member may be a blade shell, and the second member may be a blade spar.

A method and apparatus for transferring formed adhesive elements from a reservoir (30) containing plural formed adhesive elements (12) to a bonding part attachable to a glass surface or other substrate through the use of adhesives. Transfer of the formed adhesive element to the bonding part (14) is accomplished by use of a vacuum tool (10) having a vacuum outlet, an internal plenum, and a series of vacuum lines formed in an adhesive element holding face. The vacuum tool is positioned over a reservoir of formed adhesive elements. Once the formed adhesive elements have been captured by the vacuum tool (10) the tool is used to place them into contact with the heated bonding part (14) directly or indirectly by intermediate placement onto a matrix (60) having a plurality of ejector pins (72) movably fitted therein. The ejector pins move the formed adhesive elements into position against the bonding part.

A method of bonding a composite vane to at least one support. The method includes positioning an end of a vane within a support, causing an adhesive to flow between the vane and the support from an inlet to an outlet, and reversing the flow of adhesive from the outlet towards the inlet.

A method for manufacturing a blade made of a composite material for a turbine engine, in particular a turbine engine of an aircraft, wherein a reinforcing shield is attached to one edge of an airfoil, the shield having a generally elongated shape along an elongation axis of the airfoil. The shield includes at least one excess dimension so as to be able to adjust the moment weight of the blade along the axis according to the position of the shield on the edge of the axis, and the method includes a step for removing a surplus portion of the shield so s to balance the blade.

A method of bonding a composite vane to at least one support. The method includes positioning an end of a vane within a support, causing an adhesive to flow between the vane and the support from an inlet to an outlet, and reversing the flow of adhesive from the outlet towards the inlet.