Abstract: An apparatus for sorting parcels is described comprising a transport surface configured to convey parcels between a first end and a second end thereof. An opening defined in the transport surface is dimensioned to receive one or more of the parcels therethrough. The transport surface comprises a plurality of surface segments having a selected geometry and surface characteristics for controlling speeds of the parcels as they are conveyed. The apparatus further comprises a routing manifold having a chute having an inlet registered with the opening, a plurality of outlets coupled to the inlet, and a first diverter system comprising one or more diverters disposed in the routing manifold and operable to selectively direct the received parcels toward any outlet of the plurality of outlets. The one or more diverters may be responsive to destination information associated with the individual parcels.

Abstract: An apparatus for sorting parcels is described comprising a transport surface configured to convey parcels between a first end and a second end thereof. An opening defined in the transport surface is dimensioned to receive one or more of the parcels therethrough. The transport surface comprises a plurality of surface segments having a selected geometry and surface characteristics for controlling speeds of the parcels as they are conveyed. The apparatus further comprises a routing manifold having a chute having an inlet registered with the opening, a plurality of outlets coupled to the inlet, and a first diverter system comprising one or more diverters disposed in the routing manifold and operable to selectively direct the received parcels toward any outlet of the plurality of outlets. The one or more diverters may be responsive to destination information associated with the individual parcels.

Abstract: A composite component includes a component body and a datum feature. The datum feature projects in a first direction from a surface of the component body; the component further includes a plurality of pins extending generally in the first direction so that a first end of each pin is engaged in the component body and a second end of each pin is engaged in the datum feature. The datum feature is removable from the component so as to leave the first ends of the pins engaged with the component body. The first ends of the pins may be used to identify and locate the position of the original datum feature, when the component requires repair or other attention.

Abstract: A composite aerofoil vane for a gas turbine engine extends in use in a generally radial direction across an axially- and circumferentially-extending annular duct. The vane comprises a plurality of first reinforcing fibers extending in a generally radial direction and a plurality of second reinforcing fibers extending in generally axial and circumferential directions. The second fibers are interlaced with the first fibers so as to form a more unified and integrated structure, and to prevent the first reinforcing fibers from moving relative to one another.

Abstract: A composite component includes a component body and a datum feature. The datum feature projects in a first direction from a surface of the component body; the component further includes a plurality of pins extending generally in the first direction so that a first end of each pin is engaged in the component body and a second end of each pin is engaged in the datum feature. The datum feature is removable from the component so as to leave the first ends of the pins engaged with the component body. The first ends of the pins may be used to identify and locate the position of the original datum feature, when the component requires repair or other attention.

Abstract: The present invention provides an article comprising a core of a core composite material sandwiched between opposing skins formed of a skin composite material. The opposing skins are separated by said core in a through-thickness (z) direction of the article. The skin composite material comprises skin fibres aligned in a plane, the plane being orthogonal to the through-thickness direction. The core composite material comprises core fibres having an extension in a direction extending between said opposing skins. The core composite material may be a 3D composite material or may comprise a laminated stack of Pre-cured Profile Cut flat Laminate (PPCL) sheets.

Abstract: A method is described in which a composite tape or sheet is processed such that it has an improved drapability when applied to a former having a complex geometrical form. The tape or sheet is selectively perforated across its width as it is dispensed, with a suction force being subsequently applied over the tape's surface to thereby cause stretching of the tape. The degree of stretching varies across the width of the tape in proportion to the degree and local density of the selective perforations.

Abstract: A composite aerofoil, the aerofoil having a leading edge, a trailing edge a pressure side and a suction side and comprising an outer erosion protection layer along one or both of the pressure side or suction side, a structural core having a plurality of resin impregnated plies of unidirectional fibers, and between the outer erosion protection layer and the structural core a woven composite impregnated with a resin having a modulus of elasticity greater than that of the resin impregnating the plies in the structural core.

Abstract: A composite material and method for manufacturing the material, the material including: a plurality of plies layered one on top of the other; and one or more through-thickness fibers which join one or more of the plurality of plies to one another; wherein the one or more through-thickness fibers form a boundary which delineates one or more discrete regions of the material.

Abstract: A method is described in which a composite tape or sheet is processed such that it has an improved drapability when applied to a former having a complex geometrical form. The tape or sheet is selectively perforated across its width as it is dispensed, with a suction force being subsequently applied over the tape's surface to thereby cause stretching of the tape. The degree of stretching varies across the width of the tape in proportion to the degree and local density of the selective perforations.

Abstract: A composite aerofoil vane for a gas turbine engine extends in use in a generally radial direction across an axially- and circumferentially-extending annular duct. The vane comprises a plurality of first reinforcing fibres extending in a generally radial direction and a plurality of second reinforcing fibres extending in generally axial and circumferential directions. The second fibres are interlaced with the first fibres so as to form a more unified and integrated structure, and to prevent the first reinforcing fibres from moving relative to one another.

Abstract: A fiber cutting device and method for cutting one or more exposed portions of a through-thickness fiber in a surface of a composite material, the device including: a cutting element for cutting the one or more exposed portions; a suction device which is operable to extract the cut exposed portions from the surface of the composite material; and a storage device for receiving the cut exposed portions.

Abstract: A method of manufacture of a composite material is provided. The method includes providing a deformable body having substrate and matrix materials on a surface of a first tool. The substrate material is loosely bound by the matrix material and may include a composite pre-form. The relative movement between the first tool and a second tool is controlled so as to apply pressure to the body between opposing surfaces of the first and second tools and thereby debulk and/or consolidate said body. The first or second tool includes a plurality of individually controllable tool elements, the temperature and/or displacement of said elements being controlled to generate a desired profile in said body. An adaptive debulking system and tool are also disclosed.

Abstract: A composite aerofoil, the aerofoil having a leading edge, a trailing edge a pressure side and a suction side and comprising an outer erosion protection layer along one or both of the pressure side or suction side, a structural core having a plurality of resin impregnated plies of unidirectional fibres, and between the outer erosion protection layer and the structural core a woven composite impregnated with a resin having a modulus of elasticity greater than that of the resin impregnating the plies in the structural core.

Abstract: A composite material and method for manufacturing the material, the material including: a plurality of plies layered one on top of the other; and one or more through-thickness fibres which join one or more of the plurality of plies to one another; wherein the one or more through-thickness fibres form a boundary which delineates one or more discrete regions of the material.

Abstract: A fibre cutting device and method for cutting one or more exposed portions of a through-thickness fibre in a surface of a composite material, the device including: a cutting element for cutting the one or more exposed portions; a suction device which is operable to extract the cut exposed portions from the surface of the composite material; and a storage device for receiving the cut exposed portions.

Abstract: A composite aerofoil, the aerofoil having a leading edge, a trailing edge a pressure side and a suction side and comprising an outer erosion protection layer along one or both of the pressure side or suction side, a structural core having a plurality of resin impregnated plies of unidirectional fibers, and between the outer erosion protection layer and the structural core a woven composite impregnated with a resin having a modulus of elasticity greater lower than that of the resin impregnating the plies in the structural core.