Rolls-royce Corporation

Jonathan V Watson

Jack Francis Colebrooke

Daniel Blacker

Conor Hickey

Hugh J Blakemore

Robert A Barker

Alexander L Fry

Adrian M Manser

Jamie W Gallagher

James Thorp

Marie-Océane Parent

A gas turbine engine comprises, in axial flow sequence, a fan assembly, a compressor module, a turbine module, and an exhaust module. The gas turbine engine comprises first and second engine mount planes. The first and second engine mount planes are configured to support gas turbine engine in machine body. The gas turbine engine has axial length L, with axial length extending from inlet face of engine to exhaust face of engine. The first engine mount plane is positioned axially along gas turbine engine at first engine mount plane position, with first engine mount plane position within a range of between 0.24*L to 0.32*L from the inlet face of the engine. The second engine mount plane is positioned axially along gas turbine engine at second engine mount plane position, with second engine mount plane position within a range of between 0.73*L to 0.79*L from the inlet face of the engine.

Gas turbine engine

An exhaust nozzle assembly for a gas turbine engine. The assembly includes concentrically arranged inner mixer and outer exhaust nozzles, the exhaust nozzle extending axially downstream of said mixer nozzle. A centre-body is axially mounted within and extends axially downstream from the mixer nozzle. A core flow duct is defined by the mixer nozzle and the centre-body, the core flow duct having a core exit area. An exhaust duct is defined at least in part by the exhaust nozzle downstream of the mixer nozzle, the exhaust duct having an exhaust exit area. The mixer nozzle includes a mixer cowl which is axially-translatable along the centre axis and the exhaust nozzle includes an exhaust cowl which is either axially-translatable along or angularly-adjustable relative to the centre axis. The assembly further includes an actuation mechanism and the mixer cowl and exhaust cowl are movable by the actuation mechanism.

Exhaust nozzle assembly

A nozzle for a gas turbine engine. An array of convergent petals hingedly coupled to a nozzle exit of fixed diameter. An array of divergent petals, each divergent petal hingedly coupled to one of the array of convergent petals. A cam surface associated with the array of convergent petals. A pivot point coupled to the array of divergent petals by a first linkage and to a fixed point by a second linkage. A cam follower coupled to the second linkage by a third linkage, the cam follower arranged to abut and travel in contact with the cam surface. An actuator coupled to the cam follower and arranged to translate the cam follower along the cam surface to move the convergent and divergent petals.

Nozzle with variable throat and exit areas

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Bristol, United Kingdom

Jonathan V Watson