Structurally enhanced preformed layers of multiple rigid unidirectional rods are constructed and arranged for use in fabricating load-bearing support structures and reinforcements in a variety of composite components, e.g. wind turbine blades. Individual preform layers include multiple elongate unidirectional strength elements or rods arranged in a single layer along a longitudinal axis of the preform layer. Individual rods include aligned unidirectional structural fibers embedded within a matrix resin such that the rods have a substantially uniform distribution of fibers and high degree of fiber collimation. The relative straightness of the fibers and fiber collimation provide rods and the preform layers with high rigidity and significant compression strength. A plurality of rods are loosely attached, e.g. knitted, together with a coupling that allows for each rod to be axially displaced, e.g. slideable, relative to another rod.

Compaction systems and methods of compacting components are provided. In one aspect, a laminate of a component can be laid up on a tool of a compaction system. The laminate defines a cavity. A noodle is positioned relative to or in the cavity. A noodle ring is then positioned relative to the noodle. For instance, the noodle ring can be placed over the noodle. A cross section of the noodle ring can be shaped complementary to a cross section of the noodle. A plunger of the compaction system is moved so that it engages the noodle ring. Particularly, the plunger is moved in such a way that a force is applied on the noodle ring so that the noodle ring compacts the noodle into the cavity.

Disclosed is a method for producing components from fiber-reinforced thermoplastic. The method involves manufacturing a multitude of semifinished products, each of which includes a plurality of impregnated fabric layers that are joined to one another only locally, as well as a frame structure having at least one cutout. The semifinished products are consolidated using a consolidation device, an inlay element being placed in each cutout before the semifinished products are consolidated.

A composite component comprising fibres embedded in a matrix material. A plurality of pins extend through the matrix material. Each pin of the plurality of pins comprises a hollow bore such that the bore of each pin defines a plurality of holes in the composite component.

Patent of invention for “automated process for manufacturing items of furniture in an integrated manufacturing cell and integrated cell for manufacturing items of furniture”. There is described an automated process for manufacturing items of furniture in an integrated manufacturing cell, the process comprising the following steps: a) Initial machining of plate (P) according to a manufacturing program, generating channels and holes; b) Installing inserts in the holes generated in the initial machining and applying resin in at least one side hole of the insert; c) Applying edging resin inside the channels generated in the initial machining; d) Curing the edging resin and resin of the inserts in a heated environment; e) Final machining of plate (P) generating at least one item of furniture. There is also described an integrated cell for manufacturing items of furniture (100), comprising a machining station (200) and a curing station (50) associated with each other by way of a transfer module (30).

A method of manufacturing is presented. The method includes providing a plurality of structural layers comprising a plurality of composite rods, wherein at least one structural layer from the plurality of structural layers is attached to a separation layer. The method further includes stacking the plurality of structural layers, detaching the separation layer from the at least one structural layer, and curing the plurality of structural layers to form a structural component of a wind turbine blade.

A reinforcing article (10, 100, 200) includes a porous substrate layer (105, 205) and a plurality of parallel first continuous fiber elements (12, 114, 212) spaced apart from each other and extending along a first direction and fixed to the porous substrate (105, 205). Each first continuous fiber element (12, 114, 212) includes a plurality of parallel and co-extending continuous fibers (22, 122, 222) embedded in a thermoplastic resin (24, 124, 224).

A method for producing a Fiber Metal Laminate component of an airplane, using a manipulator system with an end effector and a control, wherein at least one metal layer and at least one unhardened fiber layer are being stacked onto each other in a mould in a stacking sequence, wherein each stacking cycle comprises picking up a metal layer or a fiber layer from a supply stack according to the stacking sequence, transporting the layer to the mould, placement of the layer at a deposition surface in the mould and depositing the so placed layer onto the deposition surface. After being picked up from the supply stack and before being deposited onto the deposition surface the layer to be stacked can be deformed by the end effector as to adapt the form of the layer to the form of the deposition surface.

A method of fabricating a fan case for a gas turbine engine defines a metallic ring including an outer surface and an inner surface. A first composite material is assembled about the outer surface of the metallic ring. A second composite material is assembled about the first composite material. The first composite material and the second material are cured about the metallic ring within a tool to form a first subassembly. The first subassembly is removed from the tool. A fan case assembly for a gas turbine engine and a gas turbine engine are also disclosed.

A composite material body (10) includes a first material layer (20) and a second material layer (30) overlapping the first material layer (20). The first material layer (20) and the second material layer (30) are wound to form a flexible and circular rod. Impact absorption is effectively improved and impact resisting strength is enhanced because energy-absorber or damping material or its composition is attached into the composite material body (10). Technical characteristics, effects and objects of this invention are achieved thereby.