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.

An end of arm tool (EOAT) for use during manufacture of parts using one or more pre-impregnated composite plies is disclosed. In an embodiment, the EOAT includes a mechanical gripper arrangement with first and second fingers configured to supply a compressive force to grip a pre-impregnated composite ply therebetween. At least one of the first and second fingers include a roller member to engage opposite surfaces of the pre-preg ply and supply a compressive gripping force. The roller member on either or both the first and second fingers preferably include a torque regulator to selectively adjust an associated roller member's resistance to rotation via supply of a rotational torque resistance.

An overlap production method of using standard coiled material, comprising the steps of: selecting a standard coiled material, designing a pattern, laser cutting according to the design pattern, cutting or reserving spaces for inserting drawn strips, forming by staggering and overlapping each layer of standard coiled material, and inserting partial materials of a standard coiled material layer into an adjacent standard coiled material and fixing it with the partial materials of the adjacent standard coiled material, or inserting the drawn strips into the spaces reserved in each layer, and combining the composition and the base clothing to make a product. The present invention produces the product with the above production method by using standard coiled materials instead of thread or strip materials, which not only achieves the goal of higher production efficiency and lower cost, but also makes the finished products have a new staggered material effect.

The invention relates to a system and to a method for producing a rotor-blade spar cap with pultruded rods made of a fiber-reinforced material. According to the invention, the system includes at least one retaining apparatus for rotatably mounting at least one rod-layer roll with a rolled-up layer of pultruded rods arranged one beside the other, and a laminating mold for receiving layers of pultruded rods. The system further includes at least one guiding apparatus and additionally at least one trimming apparatus. The guiding apparatus is designed to guide onto the laminating mold a layer of pultruded rods which has been unrolled from a rod-layer roll. And, the trimming apparatus, for trimming the layers of pultruded rods, has a sawing apparatus and/or a milling apparatus.

A scrap collection assembly for a tape lamination head that applies a plurality of composite tape segments includes a crack-off assembly with a scrap crack-off redirect roller configured to engage one or more composite tape segments and one or more scrap portions; and a secondary crack-off roller configured to engage one or more composite tape segments and one or more scrap portions; a pivot that connects the crack-off assembly to the tape lamination head, wherein the secondary crack-off roller selectively moves about the pivot to change a direction of composite tape movement.

In an embodiment, an energy-absorbing device can comprise: a polymer reinforcement structure, wherein the polymer reinforcement structure comprises a polymer matrix and chopped fibers; and a shell comprising 2 walls extending from a back and forming a shell channel, wherein the shell comprises continuous fibers and a resin matrix; wherein the polymer reinforcement structure is located in the shell channel.

A method of manufacturing a display unit including: preparing an optical film; forming a first alignment mark on the optical film; forming a cut-out line, corresponding to a predetermined closed curve layout, on the optical film based on a position of the first alignment mark; preparing a panel having a second alignment mark; aligning the optical film and the panel based on the positions of the first alignment mark and the second alignment mark; and laminating the optical film, after the processing of forming the cut-out line, on the panel.

A disposable wearable article includes an elastic film stretchable structure in which an elastic film is laminated between a first sheet layer and a second sheet layer. The first sheet layer and the second sheet layer are bonded to each other through holes passing through the elastic film with many bonded portions arranged at intervals. A region having the elastic film stretchable structure includes a stretchable region that elastically stretches and contracts together with the elastic film. The stretchable region includes a plurality of elastic films disposed so as to have an overlapping portion. The number of laminated layers of the elastic film in a region located in an intermediate portion of the stretchable region in an orthogonal direction (XD) orthogonal to a stretchable direction (ED) is different from that in each of second regions adjacent to both sides of the first region.

According to the present invention, a system for manufacturing an optical display element, which manufactures an optical display element by laminating optical films on both planes of a rectangular panel according to the present invention includes: a panel supply unit supplying the panel; a first laminating unit laminating a first optical film onto the panel in a first direction selected from a long-edge longitudinal direction and a short-edge longitudinal direction of the panel at a first side selected from the two sides of the panel; a second laminating unit laminating a second optical film onto a plane opposite to the plane onto which the first optical film is laminated in a second direction selected from the long-edge longitudinal direction and the short-edge longitudinal direction of the panel and different from the first direction; and a first reverse unit reversing, when a first laminating plane onto which the first optical film is laminated is selected from between one plane and the other plane of the panel and predetermined as a process condition, the panel to reverse positional relationships of the planes of the panel if the first laminating plane is different from a plane of the panel supplied by the panel supply unit at the first side of the panel.

A method for managing nonconformances in laminates. The method comprises recording, by a sensor system, layup information about a layup of layers on a workpiece platform, wherein the layup of layers forms a workpiece and recording inspection information about the laminate on an inspection platform, wherein the laminate is formed from curing the workpiece. An analyzer in a computer system identifies a laminate nonconformance in the laminate using the inspection information and a user input verifies the laminate nonconformance in the laminate is present. An artificial intelligence system is trained by the computer system using the layup information, the inspection information, and the user input verifying the laminate nonconformance.