A method for forming a composite part includes positioning a composite ply over a forming surface of a forming tool, moving a forming feature into engagement with the composite ply to yield a formed ply, and, after the moving, securing the formed ply relative to the forming tool.

A composite forming apparatus includes an end effector, a forming feature that is coupled to the end effector, and a heating element that is coupled to the forming feature to heat the forming feature. The end effector moves the forming feature relative to a composite ply to form the composite ply over a forming tool or over a prior formed composite ply. The forming feature heats the composite ply via conduction.

A composite forming apparatus includes an end effector, a forming feature, and a non-contact heater. The forming feature is coupled to the end effector. The end effector moves the forming feature relative to a composite ply to form the composite ply over a forming tool or a prior formed composite ply. The non-contact heater heats to a portion of the composite ply before the portion of the composite ply is formed over the forming tool or the prior formed composite ply.

A method and system for fabricating a composite structure is provided. A first vacuum bag is laid down on a surface of a tool. A composite material is positioned on top of the first vacuum bag on the tool. A second vacuum bag covers the composite material. Vacuum pressure is applied to the first vacuum bag and the second vacuum bag. The composite material is cured to form the composite structure. The first vacuum bag is inflated with compressed air to lift the composite structure from the tool.

An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.

A method, apparatus, and system for manufacturing a composite part. A set of reference locations is identified for a set of fiducial markers on a composite ply from a ply shape model for the composite part. The set of fiducial markers is created at the set of reference locations on the composite ply. The composite ply is cut to have a shape defined by the ply shape model.

A gripping device (76) is provided for lifting a preform for a wind turbine blade from a preform mould (71). The gripping device (76) comprises a base frame (62), a plurality of arms (78) slidably mounted on the base frame (62), each arm (78) having a proximal end and a distal end, a plurality of gripping members (86) for gripping a top surface (75) of the preform. The vertical position of one or more arms (78) of the gripping device (76) relative to the base frame (62) may change when lowering the gripping device (76) towards a preform to reflect the top surface (75) of the perform.

The present invention relates to a method and mold (100, 110) for forming a thermoplastic composite (1) that has one or more inner openings (0). The present invention further relates to a thermoplastic composite (1) manufactured using such method. Typically, forming of a thermoplastic composite (1) is achieved using a mold (100, 110) comprising a first (100) and second (110) mold part that are moved towards each other for the purpose of forming the thermoplastic composite (1). According to the invention, the mold further comprises a third mold part (120) that is movably arranged around the one or more first mold parts (100). Furthermore, an additional step is used of clamping the outer part in between the second and third mold parts during the mutual movement of the first and second mold parts while allowing the one or more inner parts to move relative to the one or more first mold parts thereby increasing the one or more inner openings, respectively.

A tool for creating a self-stiffened panel, which comprises a support, a set of punches and a channel delimited between two punches, for each punch, a first securing arrangement including a slider that is able to move in translation on the support and at least one hook secured to the slider, and a second securing arrangement including at least one nose integral with the punch, and an actuating arrangement that moves the slider from a securing position in which each nose is located between the support and a hook, to a release position in which the hooks are offset with respect to the noses. With such a tool, each punch is held in position over its length, which ensures correct positioning during lay-up, even in the event of the tool being rotated.

This invention relates to a root end structure, a wind turbine blade comprising such a root end structure and a method of manufacturing such a wind turbine blade. The root end structure comprises a plurality of fastening members distributed along a root end of a blade part, wherein a first plurality of pultruded elements are arranged in between the fastening members and a second pultruded element is further arranged at the blade joint ends adjacent to an outermost fastening member. Each first pultruded element has opposite facing second sides each facing a first side of an adjacent fastening member. The second pultruded element has one second side facing the outermost fastening member and another second side facing the blade joint interface. The second pultruded element comprises a transition portion forming a smooth transition for the inner layers extending further along the mould edge surface.