A composite forming apparatus includes an end effector and a forming feature that is coupled to the end effector. The end effector moves the forming feature relative to a forming tool to form a composite ply over a forming surface of the forming tool or over previously formed composite material on the forming surface of the forming tool. The composite forming apparatus further includes a positioning member engaged with the forming feature. The engagement between the positioning member and the forming feature facilitates a position between the forming feature and the composite ply to promote uniform application of compaction force over the forming surface of the forming tool.

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.

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.

Grid structure, such as a lattice or grid-stiffened structure and a process of manufacturing such a grid structure. Fiber material is laid up on a base tool to form intersecting ribs defining a grid with a plurality of cavities. In the same step fiber material is laid to form one or more; local substructures. Blocks are placed, at the positions of the cavities. The fiber material of the ribs and. the local substructures is impregnated with a resin. Optionally, one or more layers of fiber material are placed on the base tool and/or over the ribs and the blocks to form an outer skin. The ribs, the local substructure and optionally the outer skin jointly consolidated to form, the grid, structure.

The present invention relates to an interlayer sheet for a spar cap comprising: a first fibre layer comprising a first plurality of fibres, having a first upper fibre surface and a first lower fibre surface, a second fibre layer comprising a second plurality of fibres, having a second upper fibre surface and a second lower fibre surface. The first fibre layer is arranged on top of the second fibre layer, such that the first lower fibre surface is in contact with the second upper fibre surface. The first fibre layer is of a different characteristic than the second fibre layer. Furthermore, the present invention relates to a spar cap for a wind turbine blade, comprising a plurality of pre-cured fibre-reinforced elements including at least a first pre-cured fibre-reinforced element and a second pre-cured fibre-reinforced element; and a number of interlayer sheets arranged between the plurality of pre-cured fibre-reinforced elements.

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.

The present disclosure relates to a spar cap (10) for a wind turbine blade (1000) comprising: a plurality of spar cap layers (20) and a first interlayer (30) arranged between the first spar cap layer (20a) and the second spar cap layer (20b) and comprising: a number of first interlayer areas (31), including a first primary interlayer area (31a), comprising a first number of interlayer sheets (33) comprising a first plurality of fibres (35); and a number of second interlayer areas (32), including a second primary interlayer area (32a), comprising a second number of interlayer sheets (34) comprising a second plurality of fibres (36), wherein the first number of interlayer sheets (33) is of a different characteristic than the second number of interlayer sheets (34).

A method of manufacturing a composite component according to various aspects of the present disclosure includes disposing a fiber preform in a mold. The fiber preform includes a first portion having a first edge and a second portion having a second edge. The first edge and the second edge cooperate to at least partially define a gap. One of the first portion or the second portion includes a first ferromagnetic material and the other of the first portion or the second portion includes a first magnetic or magnetizable component. The method further includes closing the gap by generating a magnetic field from the first magnetic or magnetizable component. The method further includes injecting a polymer precursor into the mold. The method further includes forming the composite component by solidifying the polymer precursor to form a polymer. The composite component includes the fiber preform and the polymer.