A method of calibrating a three-dimensional measurement system having a plurality of cameras and at least one projector is provided. The method includes performing a full calibration for each camera/projector pair where the full calibration generates at least two sets of correction matrices. Subsequently, an updated calibration is performed for each camera/projector pair. The updated calibration changes less than all of the sets of correction matrices.

A method and apparatus for sealing a bag made of a polymeric material by applying heat activated layers on different portions of the bag, wherein the first adhesive layer and the second adhesive layer have respective heat activation temperatures below the softening point temperature of the polymeric material; after creasing the bag along a fold line, applying heat at a temperature below the softening point temperature of the polymeric material to activate the first adhesive layer and the second adhesive layer to adhesive states after the bag has been filled with contents; and folding the bag to form an adhesive-to adhesive seal by contact between the heat activated first adhesive layer and the heat activated second adhesive layer.

The invention relates to a turbine engine blade, particularly made of composite material, including: on the one hand, an airfoil (10) which exhibits: a leading edge (12), a trailing edge (14) opposite to the leading edge (12), intrados (16) and extrados (18) lateral walls which connect the leading edge (12) to the trailing edge (14), et on the other hand, a structural reinforcement (20) including a base (24) extending into two fins (26, 28) and designed to be applied to the leading edge (12) and the lateral walls (16, 18) of the airfoil (10), characterized in that the fins (26, 28) of the structural reinforcement (20) and/or the lateral walls (16, 18) of the airfoil (10) are shaped to maintain an assembly space (30) with nonzero thickness between at least one of the fins (26, 28) and the airfoil (10) when the structural reinforcement (20) is in place on the airfoil (10), said assembly space (30) extending from a free end (27, 29) of said fin (26, 28) toward the base (24) of the structural reinforcement (20).

Aspects of the present disclosure generally describe polyarylether ketones and methods of use. In some aspects, a composition includes one or more polymers of formula (IV):

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A wind turbine with a wind turbine tower, a nacelle on the tower, a rotor hub rotatably mounted to the nacelle, and at least one wind turbine blade having a blade root mounted to the rotor hub, a tip end, a pressure side and a suction side connected to each other via a leading edge and a trailing edge, a first shell part having inner and outer surfaces and a second shell part having inner and outer surfaces, the shell parts having flanges that extend outwards from the trailing edge of the shell parts and away from the outer surface with gluing surfaces which are glued together when the two shell parts are placed on top of each other. This allows the glue line to be moved out of the inner area defined by the shell parts so that the glue process can be controlled more effectively.

A method of bonding a vulcanized elastomer is provided comprising the steps of; providing an adhesive comprising a primary acrylate monomer, a reactive flexibilizing monomer, and further optionally comprising a toughener, an adhesion promoter and a free radical initiator, then depositing the adhesive on at least one surface of an elastomer or a second substrate, wherein the elastomer is a vulcanized elastomer, then bringing the elastomer substrate and second substrate together with the adhesive disposed therebetween, and allowing the adhesive to cure and bond the elastomer and second substrate together at a temperature of less than about 100° C. to produce a bonded structure.

Disclosed is a method for assembling a wind turbine blade comprising a first blade component, e.g. a first blade half shell, and a second blade component, e.g. a second blade half shell, the first blade component comprising a first contact area configured to be connected to a second contact area of the second blade component, the first contact area having a first contact surface, the second contact area having a second contact surface.

A method of making a modular wind turbine blade is described. The modular blade comprises first and second blade modules connected together by a scarf joint between tapered spar caps of the respective blade modules. According to the method, first and second blade modules are laid up in the same mould assembly. A separating layer is arranged between the layups of the first and second module in a joint region of the mould. The separating layer has a thickness corresponding to a required bond thickness in the scarf joint when the modules are bonded together.

A joint structure according to an embodiment of the present invention is provided with: a first member that is made of a metal material and has a plurality of holes having an opening diameter of 30-100 μm formed in a surface thereof; a third member that is made of a metal material the same as or different from that of the first member, or a thermoplastic resin, and that has a plurality of independent holes having an opening diameter of 30-100 μm formed in a surface thereof; and a second member that is made of a curable resin and joins the surface of the first member in which the holes are formed and the surface of the third member in which the holes are formed.

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.