Abstract: A method of sealing one or more openings provided in a wall of an aerofoil for a gas turbine engine, the aerofoil comprising at least one cavity which is at least partly filled with a vibration damping material, the method comprising steps to provide a metallic material onto the wall of the aerofoil in order to cover the opening and bond the metallic material to the wall of the aerofoil to seal the opening.

Abstract: A gas turbine engine comprises a gearbox comprises a sun gear, an annulus gear, a plurality of planet gears and a carrier. The sun gear meshes with the planet gears and the planet gears mesh with the annulus gear. The planet gear carrier comprising a first ring, a second ring spaced axially from the first ring and a plurality of circumferentially spaced axles extending axially between the first ring and the second ring. Each planet gear is rotatably mounted on a respective one of the axles and the axles are arranged at a first radius. At least one of the first ring and the second ring comprises a metal matrix composite material ring and the metal matrix composite ring comprises a ring of reinforcing fibres and the ring of reinforcing fibres having a second radius greater than the first radius.

Abstract: A gas turbine engine comprises a gearbox comprises a sun gear, an annulus gear, a plurality of planet gears and a carrier. The sun gear meshes with the planet gears and the planet gears mesh with the annulus gear. The planet gear carrier comprising a first ring, a second ring spaced axially from the first ring and a plurality of circumferentially spaced axles extending axially between the first ring and the second ring. Each planet gear is rotatably mounted on a respective one of the axles and the axles are arranged at a first radius. At least one of the first ring and the second ring comprises a metal matrix composite material ring and the metal matrix composite ring comprises a ring of reinforcing fibres and the ring of reinforcing fibres having a second radius greater than the first radius.

Abstract: A method of sealing one or more openings provided in a wall of an aerofoil for a gas turbine engine, the aerofoil comprising at least one cavity which is at least partly filled with a vibration damping material, the method comprising steps to provide a metallic material onto the wall of the aerofoil in order to cover the opening and bond the metallic material to the wall of the aerofoil to seal the opening.

Abstract: A fan disc is provided for supporting fan blades of a gas turbine engine. The fan disc has a disc body having axially extending slots for receiving, in use, dovetail root fixings of a circumferential row of fan blades. The fan disc further has an annular drive arm which extends radially inwardly from a forward portion of the disc body to a connector for engaging, in use, with a corresponding connector portion of a drive shaft of the engine. The fan disc further has a hoop stiffening ring which is removably mounted to a rear portion of the disc body, the stiffening ring being axially spaced from the drive arm to increase the torsional stiffness of the fan disc.

Abstract: A fan blade root block assembly includes a fan blade, and a cheek piece. The fan blade includes a first root portion having a first root portion end, and a second root portion having a second root portion end. The first root portion is aligned side by side with the second root portion, and the cheek piece is attached to each of the first root portion end and the second root portion end.

Abstract: Method of manufacturing a metal matrix composite component includes the steps of providing a first tubular member having a first end and an opposite second end, the first tubular member's first end being formed as a first end block; positioning a metal matrix composite tubular member concentrically the first tubular member; positioning a second tubular member concentrically over metal matrix composite tubular member, second tubular member having a first end and an opposite second end, the second tubular member's second end being formed as a second end block; welding first tubular member's first end to the second tubular member's first end, and the first tubular member's second end to second tubular member's second end, to join the first and second tubular member and thereby to form a metal matrix composite preform; and consolidating metal matrix composite preform by a hot isostatic pressing process to form the metal matrix composite component.

Abstract: A fan disc is provided for supporting fan blades of a gas turbine engine. The fan disc has a disc body having axially extending slots for receiving, in use, dovetail root fixings of a circumferential row of fan blades. The fan disc further has an annular drive arm which extends radially inwardly from a forward portion of the disc body to a connector for engaging, in use, with a corresponding connector portion of a drive shaft of the engine. The fan disc further has a hoop stiffening ring which is removably mounted to a rear portion of the disc body, the stiffening ring being axially spaced from the drive arm to increase the torsional stiffness of the fan disc.

Abstract: A rotor 10 for an electrical machine comprising a rotor body 12, at least one magnet 18 coupled to the rotor body 12 and a retainer 22 for retaining the at least one magnet 18 to the rotor body 12, the retainer 22 comprising at least one elongate fibre in a metal matrix.

Abstract: A ceramic fibre reinforced metal rotor is manufactured from a first metal ring, a second metal ring and a plurality of fibre preforms. Each fibre preform includes a metal coated ceramic fibre arranged in a spiral. An annular groove is formed in an axial face of the first metal ring and the fibre preforms are arranged in the annular groove. An annular projection is formed on an axial face of the second metal ring and two annular grooves are formed on opposite radial sides of the annular projection. The second metal ring is arranged such that the annular projection is aligned with the annular groove of the first metal ring. Heat and pressure is applied to axially consolidate the fibre preforms and to bond the first metal ring, the second metal ring and the fibre preforms to form a unitary composite component. The grooves allow axial movement of the projection and control consolidation.

Abstract: A ceramic fibre reinforced metal rotor with integral rotor blades is manufactured using a continuous strip of unidirectional ceramic fibres in a metal matrix. The continuous strip of ceramic fibres in a metal matrix is cut into a plurality of separate pieces of predetermined length. The separate pieces of ceramic fibres in the metal matrix are arranged alternately in a spiral, with separate pieces of unreinforced metal matrix in adjacent abutting relationship to form a ring which has a plurality of laminations. The ring of laminations of metal matrix composite pieces and unreinforced metal matrix pieces are arranged between an inner and an outer metal ring to form an assembly. The assembly is consolidated by hot isostatic pressing using radially applied pressure. The separate pieces of metal matrix composite provide compliance to reduce breaking or buckling of the fibres, and the pieces of unreinforced metal matrix prevents damage spreading between laminations.

Abstract: A ceramic fibre reinforced metal rotor with integral rotor blades is manufactured using a continuous strip of unidirectional ceramic fibres in a metal matrix. The continuous strip of ceramic fibres in the metal matrix is cut into a plurality of separate pieces of predetermined length. The separate pieces of ceramic fibres in the metal matrix are arranged alternately in a spiral, with separate pieces of unreinforced metal matrix in adjacent abutting relationship to form a ring which has a plurality of laminations. The ring of laminations of metal matrix composite pieces and unreinforced metal matrix pieces are arranged between an inner and an outer metal ring to form an assembly. The assembly is consolidated by hot isostatic pressing using radially applied pressure. The separate pieces of metal matrix composite provide compliance to reduce breaking or buckling of the fibres, and the pieces of unreinforced metal matrix prevents damage spreading between laminations.

Abstract: Known methods of melting Titanium and its alloys for the purpose of sheathing a ceramic filament include the premelting of the metal in a crucible. This method results in contamination of the metal. The present invention obviates the crucible and instead positions a rod of solid Titanium or an alloy thereof adjacent the filament and locally heats the end of the rod. The melt continuously coats the filament which is then traversed laterally of the rod. The method is employed in an inert atmosphere and contamination is thus avoided. In a preferred embodiment, a computer controls the rate of melting of the rod, the movement of the rod, and the lateral movement of the filament.