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 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 reinforcing structure for a wind turbine blade is in the form of an elongate stack of layers of pultruded fibrous composite strips supported within a U-shaped channel. The length of each layer is slightly different to create a taper at the ends of the stack; the centre of the stack has five layers, and each end has a single layer. The ends of each layer are chamfered, and the stack is coated with a thin flexible pultruded fibrous composite strip extending the full length of the stack. The reinforcing structure extends along a curved path within the outer shell of the blade. The regions of the outer shell of the blade on either side of the reinforcing structure are filled with structural foam, and the reinforcing structure and the foam are both sandwiched between an inner skin and an outer skin.

A method for manufacturing an engineered stone, the method including: providing a mixture comprising at least a stone or stone like material and a binder; compacting the mixture; curing the binder; and printing on at least a top surface of the engineered stone.

A method for manufacturing an engineered stone, the method including: providing a mixture comprising at least a stone or stone like material and a binder; compacting the mixture; curing the binder; and printing on at least a top surface of the engineered stone.

Provided are stiffened stringer panels with integrated plank structures. An example composite panel comprises a skin member having an inner surface, and a plank on the inner surface. The plank comprises a set of layered laminate plies and extends from a first side to a second side. Each laminate ply of the set of layered laminate plies is sized to form a desired geometric profile for each of the first side and the second side. The composite panel further comprises a stringer including a cap portion that spans from the first side of the plank to the second side of the plank to form a first flange portion and a second flange portion, respectively, on the inner surface of the skin member. Base segments of the cap portion conform to the desired geometric profile of respective first and second sides of the plank.

A method for manufacturing a composite part by laying up courses of composite tape using an automated tape layup (ATL) machine onto a conductive flexible facesheet laid flat on a flat surface, and then transferring the facesheet with the composite material thereon to a curved tooling surface for attachment of substructures and curing into the composite part. The method may also include applying insulation below the facesheet and above the composite material, then heating the conductive facesheet to cure the composite tape and fuse the composite tape to the substructures without heating the tooling surface or any other items used to compress and cure the composite material into the composite part. Heating of the facesheet may be performed using joule heat provided by a single turn transformer inducing current to a plurality of conductive wires attached at opposing ends to the facesheet.

A method for manufacturing a composite part by laying up courses of composite tape using an automated tape layup (ATL) machine onto a conductive flexible facesheet laid flat on a flat surface, and then transferring the facesheet with the composite material thereon to a curved tooling surface for attachment of substructures and curing into the composite part. The method may also include applying insulation below the facesheet and above the composite material, then heating the conductive facesheet to cure the composite tape and fuse the composite tape to the substructures without heating the tooling surface or any other items used to compress and cure the composite material into the composite part. Heating of the facesheet may be performed using joule heat provided by a single turn transformer inducing current to a plurality of conductive wires attached at opposing ends to the facesheet.

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.

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.