Abstract: The invention relates to a gas turbine engine, in particular an aircraft engine, comprising: a turbine connected via an input shaft device to a gearbox device having a sun gear, a planet carrier having a plurality of planet gears attached thereto, and a ring gear, the sun gear is connected to the input shaft device, the planet carrier or the ring gear is connected to a propulsive fan via an output shaft device of the gearbox device, with an inter-shaft bearing system being positioned radially between the input shaft device and the planet carrier of the gearbox device.

Abstract: A gas turbine engine, including: a low pressure spool having a low pressure compressor and a low pressure turbine connected by a low pressure shaft; a reduction gear train having a sun gear, a carrier having a plurality of planet gears attached thereto, and a ring gear, wherein one of the sun gear, carrier or ring gear is connected to the low pressure shaft, and another of the sun gear, carrier and ring gear provides an output drive; a propulsive fan mounted fore of the gear train; a fan shafting arrangement comprising a fan shaft which is connected to the output drive of the gear train and a fan support shaft which passes through center of the gear train along the axis of rotation of the gearbox and fan, wherein the fan shafting arrangement is rotatably supported by at least two axially separated bearings.

Abstract: A gas turbine engine, including: a low pressure spool having a low pressure compressor and a low pressure turbine connected by a low pressure shaft; a reduction gear train having a sun gear, a carrier having a plurality of planet gears attached thereto, and a ring gear, wherein one of the sun gear, carrier or ring gear is connected to the low pressure shaft, and another of the sun gear, carrier and ring gear provides an output drive; a propulsive fan mounted fore of the gear train; a fan shafting arrangement comprising a fan shaft which is connected to the output drive of the gear train and a fan support shaft which passes through centre of the gear train along the axis of rotation of the gearbox and fan, wherein the fan shafting arrangement is rotatably supported by at least two axially separated bearings.

Abstract: A gas turbine engine, including: low pressure spool having low pressure compressor and low pressure turbine connected by low pressure shaft; reduction gear train having sun gear, a carrier having a plurality of planet gears attached thereto, and a ring gear, wherein the sun gear, carrier or ring gear is connected to the low pressure shaft, and another of the sun gear, carrier and ring gear provides an output drive; a propulsive fan mounted fore of the gear train; a fan shafting arrangement comprising a fan shaft connected to the output drive of the gear train via a coupling, wherein the coupling includes a connection point to the fan shaft at a first end, and a connection point to the gear train at a second end wherein the first and second end are axial separated and radially separated and the axial separation is greater than the radial separation.

Abstract: A catcher ring assembly (170) configured to limit axial movement of a turbomachine shaft assembly (132, 132?) during a failure mode, the catcher ring assembly comprising a catcher ring (172) disposable about and connectable to the shaft assembly, wherein one of the shaft assembly and the catcher ring comprises a protrusion (194, 182) and the other of the shaft assembly and the catcher ring comprises a recess (192, 184), the recess corresponding in shape to the protrusion, wherein the protrusion and recess are circumferentially disposed about a longitudinal axis of the shaft assembly and the protrusion extends in an axial direction.

Abstract: A bladed rotor comprises a rotor body 2 carrying blades 6, whose pitch can be varied by means of a pitch input shaft 10. The pitch input shaft 10 drives the respective blade 6 about a spanwise axis X of the blade through a harmonic drive reduction gear 14. The harmonic drive reduction gear 14 comprises a wave generator 16 which is fixed for rotation on the pitch input shaft 10 and a flex spline which meshes with a circular spline 20 and is secured to the blade 6.

Abstract: A back-up featherer is provided for an engine arrangement having a main hydraulic actuator which operates a pitch change mechanism to angularly displace propellers of a propeller assembly of the engine arrangement, the pitch change mechanism and main hydraulic actuator rotating with the propeller assembly. The back-up featherer has one or more back-up hydraulic actuators located on a static structure of the engine arrangement. The back-up featherer further has one or more load application members which are located on the static structure of the engine arrangement and which are movable by the back-up hydraulic actuators. When moved by the back-up hydraulic actuators, the load application members bear against an engagement portion of the pitch change mechanism across a rotating interface formed therebetween to apply a load to the pitch change mechanism which results in angular displacement of the propellers.

Abstract: A gas turbine engine arrangement comprises a first gas turbine engine, a second gas turbine engine, a differential gearbox and an electrical generator. The differential gearbox has a first input drive, a second input drive and an output drive. The output drive of the differential gearbox is arranged to drive the electrical generator via an external, accessory, gearbox. The external, accessory, gearbox drives other accessories. The first gas turbine is arranged to drive the first input drive of the differential gearbox and the second gas turbine engine is arranged to drive the second input drive of the differential gearbox. The electrical generator and accessories are driven at a constant frequency speed/frequency.

Abstract: A catcher ring assembly (170) configured to limit axial movement of a turbomachine shaft assembly (132, 132?) during a failure mode, the catcher ring assembly comprising a catcher ring (172) disposable about and connectable to the shaft assembly, wherein one of the shaft assembly and the catcher ring comprises a protrusion (194, 182) and the other of the shaft assembly and the catcher ring comprises a recess (192, 184), the recess corresponding in shape to the protrusion, wherein the protrusion and recess are circumferentially disposed about a longitudinal axis of the shaft assembly and the protrusion extends in an axial direction.

Abstract: A bladed rotor comprises a rotor body 2 carrying blades 6, whose pitch can be varied by means of a pitch input shaft 10. The pitch input shaft 10 drives the respective blade 6 about a spanwise axis X of the blade through a harmonic drive reduction gear 14. The harmonic drive reduction gear 14 comprises a wave generator 16 which is fixed for rotation on the pitch input shaft 10 and a flex spline which meshes with a circular spline 20 and is secured to the blade 6.

Abstract: A back-up featherer is provided for an engine arrangement having a main hydraulic actuator which operates a pitch change mechanism to angularly displace propellers of a propeller assembly of the engine arrangement, the pitch change mechanism and main hydraulic actuator rotating with the propeller assembly. The back-up featherer has one or more back-up hydraulic actuators located on a static structure of the engine arrangement. The back-up featherer further has one or more load application members which are located on the static structure of the engine arrangement and which are movable by the back-up hydraulic actuators. When moved by the back-up hydraulic actuators, the load application members bear against an engagement portion of the pitch change mechanism across a rotating interface formed therebetween to apply a load to the pitch change mechanism which results in angular displacement of the propellers.

Abstract: A gas turbine engine arrangement (1) comprises a first gas turbine engine (10), a second gas turbine engine (70), a differential gearbox (57) and an electrical generator (112). The differential gearbox (57) has a first input drive (54), a second input drive (78) and an output drive (110). The output drive (110) of the differential gearbox (57) is arranged to drive the electrical generator (112) via an external, accessory, gearbox (56). The external, accessory, gearbox (56) drives other accessories (116, 120). The first gas turbine (10) is arranged to drive the first input drive (54) of the differential gearbox (57) and the second gas turbine engine (70) is arranged to drive the second input drive (78) of the differential gearbox (57). The electrical generator (112) and accessories (116, 120) are driven at a constant frequency speed/frequency.

Abstract: A method for creating a layout includes the steps of retrieving selected object data, displaying related object data associated with the selected object data, and linking selected related object data to the selected object data to create a layout. Diagrams of engines showing interconnections and layouts of the engines are thus quickly and efficiently generated. Simulations of the layouts are also provided for diagnosis of engine problems.

Abstract: Apparatus and a method for rapidly replacing a tool set included in a bodymaker are disclosed. A bodymaker is used in connection with tin box manufacture and typically includes a mandrel and a set of forming wings disposed above the mandrel and specifically designed for a particular shape of mandrel so that a planar bland disposed above the mandrel can be formed therearound by the forming wings. A support plate mounted on a totally and translatable axially of the mandrel on guide means is rolled into place adjacent the tool set, and the support plate is moved towards the free ends of the tools within the set and connected within the bodymaker. As the support plate approaches the free ends of the tools, latch means provided on the support plate in front of a suitably shaped recess are deflected laterally by a plug formation provided at least on the mandrel.

Abstract: Apparatus for seaming an end E to an open end of a container body B in at least first and second seaming operations comprises a lifter pad to support the container body, a seaming chuck to support the end in place on the container body, and an annular seaming tool having at least first and second annular seaming profiles on its inner surface which surrounds the end. The apparatus includes drive means for providing relative rolling movement between the seaming tool and the end in which the drive means drives the annular seaming tool to gyrate around the can end. Means are also provided for causing relative movement between the end and the annular seaming tool, from a first relative position in which the first seaming profile can contact the end E to perform the first seaming operation, to at least a second relative position in which the second seaming profile can contact the end E to perform the second seaming operation.

Abstract: Apparatus for seaming a container end E to an open end of a container body B, comprises a pad to support the container body, a seaming chuck to support the end E in place on the container body B and cooperating with the pad to hold the container body and end one against the other, and an annular seaming tool having two annular seaming profiles on its inner surface which surrounds the end for progressively folding peripheral portions of the container body and end together to form a seam. The annular seaming tool is mounted on a tool holder and means are provided for supporting and driving the tool holder in orbiting motion such that the axis of the seaming tool follows a circular path around the axis of the seaming chuck. The seaming tool is mounted on the apparatus for free rotation about its axis such that when the seaming profile engages the peripheral portions of the container end, it is free to roll around the end to form the seam progressively.

Abstract: A ram (40,50) of a press comprises metal sleeve (41,51), a hollow core (42, 58), a first end piece 42A, 52 attached to one end of the rod and a second end piece 46, 54 attached to the other end 47 of the ram to support a tool, the hollowcore being made of a material lighter than that of the sleeve. The benefit is a ram of reduced weight to minimize inertia forces arising during use.