Walls of gas turbine engine casings, fan cases, and methods for forming walls, e.g., fan case walls, are provided. For example, a wall comprises a plurality of composite plies arranged in a ply layup. The wall is annular and circumferentially segmented into a plurality of regions that include at least one first region and at least one second region. The ply layup in the first and second regions is different such that the ply layup is non-axisymmetric. An exemplary fan case comprises an annular inner shell, a filler layer, an annular back sheet, and an annular outer layer. The back sheet is circumferentially segmented into a plurality of regions, including at least one first region and at least one second region, and comprises a plurality of composite plies arranged in a ply layup that is different in the first and second regions such that the ply layup is non-axisymmetric.

A method of manufacturing a tiltrotor wing structure including providing a spar mold having a plurality of bores extending from an exterior surface of the mold to an interior surface of the mold, the plurality of bores corresponding to a plurality of primary coordination holes in a spar member, the spar mold having a periphery defined by a top edge, a bottom edge and outboard ends; selecting a plurality of resin impregnated plies to ensure that the plies continuously extend beyond the periphery of the spar mold; laying the plies in the spar mold; curing the plies in the mold to form a cured spar member that extends beyond the periphery of the spar mold; and accurately drilling a plurality of primary coordination holes in the cured spar member in the spar mold using a tool positioned in the plurality of bores.

An impregnation system and a method for impregnating a textile fabric for composite components are described. A matrix 2 can be applied to a textile fabric 1 in such a way that the matrix 2 penetrates it at least partially and/or at least on one side. A first and a second endless belt 1 each designed as a belt loop are provided for the impregnation system. Between the first 4 and the second belt loop 5, the textile fabric 1 can guided on the mutually facing surfaces 6 of the belt loops and can be impregnated there. The deflection rollers 7 are provided in the respective belt loop 4, 5 of the respective endless belts at the deflection areas, with at least one roller being adjustable in the direction of the mutually facing surfaces 6 of the belt loops 4, 5. By adjusting the rollers 8 in the y direction, the wrap angle and thus the pressure exerted on the textile fabric during impregnation is controlled.

A method and apparatus is presented. A layer of composite material is laid up on a forming tool. A bend is formed in the layer on the forming tool to form a bent layer. A laminate stack and the bent layer are assembled to form the composite filler.

A method of joining a first panel and a second panel with an adhesive and flow drill screws is provided. The adhesive is applied in a continuous strip and the flow drill screws are inserted through the first panel, the continuous strip of adhesive, and through a second panel. Material displaced by the flow drill screw forms a collar. An intermediate portion of the collar defines a bond gap for the adhesive between the panels. An assembly is made according to the method includes the intermediate collar portion formed by the flow drill screw displacing material from the panels that sets a bond gap between the first and second panels for the adhesive.

A method for adjusting a sidewall unit (1) of a casting mold for concrete products, which sidewall unit comprises a support structure (2, 32, 42) and a mold surface plate (3, 3′, 33, 43) fixed to the support structure, and which sidewall unit is fixed on a casting bed (8), wherein the mold surface plate comprises at least two portions (3, 3′) extending along the length of the sidewall unit and connected to the support structure (2) and the vertical position of at least one of the portions (3), defined by orientation of the sidewall unit (1) fixed on a casting bed (8), is adjusted to form a gap (9) extending along the length of the sidewall unit between the portions. The invention also relates to such a sidewall unit.

Some embodiments of the present disclosure relate to an apparatus including an additively manufactured node having a socket. The apparatus includes a panel interconnected with node. The panel includes opposing surface layers and a core between at least a portion of the surface layers. The socket engages an end portion of the panel and shapes the surface layers on the end portion of the panel.

A fan track liner for a fan containment arrangement for a gas turbine includes a cellular impact structure and a supporting sub-laminate integrally formed with each other from fibre-reinforced material. The fan track liner further includes a ballistic barrier comprising a woven reinforcing fibre ply and a layer of reinforcing fibre felt. There is also disclosed an associated fan containment arrangement and a method of manufacturing a fan track liner.

A process for producing a component for an aircraft for the frame, e.g. formers and stringers. Aircraft are being increasingly constructed of polymeric fiber composite to reduce weight. Here, fiber composites were originally composed of thermoset polymer and carbon fibers. Thermoplastic fiber composites are increasingly a research focus. An example is poly(ether ether ketone). However, production of components of thermoplastic fiber composites is complex. An improved process for producing such components includes producing a sheet-like object with a thermoplastic fiber composite having a thermoplastic polymer material and reinforcing fibers embedded therein, forming the sheet-like object for a semifinished part, and solidification of the semifinished part to give the component. Components obtainable by this process are also disclosed.

Described is a method for producing a sandwich composite component and a sandwich composite component with a pressed two- or three-dimensional shape, having at least one structured core layer made of thermoplastic material which has two opposite core layer surfaces, each bonded to a thermoplastic cover layer. A sandwich composite component is also described.