Rolls-royce Corporation

Paul Simms

Andrew Swift

Stewart T Thornton

David Reginald Trainer

Antony Morgan

David Peter Scothern

David S Knott

Glenn A Knight

Gareth Edward Moore

Colin W R McFarlane

Stewart Thornton

Glenn Knight

Colin Mcfarlane

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.

Shafting arrangement for a gas turbine engine

A catcher ring assembly () configured to limit axial movement of a turbomachine shaft assembly () during a failure mode, the catcher ring assembly comprising a catcher ring () disposable about and connectable to the shaft assembly, wherein one of the shaft assembly and the catcher ring comprises a protrusion () and the other of the shaft assembly and the catcher ring comprises a recess (), 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.

Catcher ring assembly

A bladed rotor comprises a rotor bodycarrying blades, whose pitch can be varied by means of a pitch input shaft. The pitch input shaftdrives the respective bladeabout a spanwise axis X of the blade through a harmonic drive reduction gear. The harmonic drive reduction gearcomprises a wave generatorwhich is fixed for rotation on the pitch input shaftand a flex spline which meshes with a circular splineand is secured to the blade

Variable pitch propeller rotor

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.

Back-up featherer

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.

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Leicester, United Kingdom

Paul Simms