A method for manufacturing a structural element of a wind turbine blade including forming of at least one injection hole in at least one laminate provided on a top side of a core material of a first portion and a second portion of the structural element and a bottom side of a core material of the first portion and the second portion, so that the at least one injection hole is fluidically connected to the cavity. Further, injecting adhesive through the injection hole into the cavity, curing the adhesive injected into the cavity and thereby forming a joint between an end of the core material of the first portion and an end of the core material of the second portion. Further, a method for manufacturing a wind turbine blade and the structural element, the wind turbine blade is also provided.

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.

A bypass turbofan engine with a nacelle comprising a fan case and a thrust-reversal system. The fan case comprises an exterior wall, and the reversal system comprises a slider having an upstream frame, a downstream frame and a plurality of spars fixed between the upstream frame and the downstream frame, in which the slider is able to move between a forward position and a retracted position. The fan case comprises, at a rear edge of its exterior wall, a support. Each support comprises, for each spar, a shoe fixed to the exterior wall and positioned radially about the spar, and a skirt secured to the shoes and extending the rear edge, in which, in a forward position, the skirt bears around the downstream frame, and in which in a forward/retracted/intermediate position, the shoes are distant from the spars from the upstream frame.

A preform can be made from two different materials that do not bond together by a bi-injection process, using the same mold. First an outer preform can be fashioned first, then an inner preform molded through a center hole in the outer preform, and the preforms connected. Inner/outer preform materials can be different, e.g., PET/polyolefin or polyamide, or the same, e.g., PET/PET. To prevent mutual bonding during molding of the second, a non-stick coating can be sprayed on a surface portion of the first preform prior to molding, the second. Manufacturing order can be either outer/inner, or inner/outer, and the non-stick coating sprayed on the inside/outside of the perform first molded.

A preform can be made from two different materials that do not bond together by a bi-injection process, using the same mold. First an outer preform can be fashioned first, then an inner preform molded through a center hole in the outer preform, and the preforms connected. Inner/outer preform materials can be different, e.g., PET/polyolefin or polyamide, or the same, e.g., PET/PET. To prevent mutual bonding during molding of the second, a non-stick coating can be sprayed on a surface portion of the first preform prior to molding, the second. Manufacturing order can be either outer/inner, or inner/outer, and the non-stick coating sprayed on the inside/outside of the perform first molded.

Structures and methods for joining misaligned or dissimilar width spar caps are disclosed as having a connecting structure in a rotor blade assembly for a wind turbine, wherein a first blade segment defines a first joint end, the first blade segment having at least one spar cap. A second blade segment defines a forward end coupled to the first blade segment, the second blade segment having at least one spar cap offset from the spar cap of the adjoining first blade segment. At least one connecting structure is coupled between the adjoining spar caps of the first blade segment and the second blade segment, the connecting structure having a plurality of sequentially stacked plies configured for parallel fiber alignment with the adjoining spar caps and cross-sectional area continuity with the adjoining spar caps.

A preform can be made from two different materials that do not bond together by a bi-injection process, using the same mold. First an outer preform can be fashioned, then an inner preform molded through a center hole in the bottom of the outer preform, and the preforms connected. Inner/outer preform materials can be different, e.g., PET/polyolefin or polyamide, or same, e.g., PET/PET. To prevent mutual bonding during molding of the second, a non-stick coating can be sprayed on a surface portion of the first preform prior to molding the second. Manufacturing order can be either outer/inner, or inner/outer, and the non-stick coating sprayed on the inside/outside of the preform first molded.

A method for connecting two components is proposed where a pressure acting on an adhesive between two join partners is supported by an auxiliary body which rests on a cutout of one of the components. Both components to be connected together and the auxiliary body are covered by a vacuum film and once the air has been sucked out, the compressive force is generated below the vacuum film.

A composite member comprises first and second elongate composite elements. Each has a wedge shaped end with a complimentary tapered end surface. At least one of the components is formed of a stack of fiber layers impregnated in resin, with the tapered end surface being formed by each fiber layer extending longitudinally progressively further than the adjacent layer towards the thin end of the wedge at which the fiber layers have the greatest longitudinal extent. The components are joined at their tapered ends by an adhesive, and the properties of the cured composite material of the at least one component and/or the properties of the adhesive are different in the vicinity of the thin end of the wedge as compared to the rest of the tapered surface in order to reduce the stress concentrations in this region.

Structures and methods for joining misaligned or dissimilar width spar caps are disclosed as having a connecting structure in a rotor blade assembly for a wind turbine, wherein a first blade segment defines a first joint end, the first blade segment having at least one spar cap. A second blade segment defines a forward end coupled to the first blade segment, the second blade segment having at least one spar cap offset from the spar cap of the adjoining first blade segment. At least one connecting structure is coupled between the adjoining spar caps of the first blade segment and the second blade segment, the connecting structure having a plurality of sequentially stacked plies configured for parallel fiber alignment with the adjoining spar caps and cross-sectional area continuity with the adjoining spar caps.