Rolls-royce Corporation

Peter Kevin Beardsley

Richard Geoffrey Stretton

Kenneth Franklin Udall

David Michael Beaven

Glenn A Knight

Crispin David Bolgar

John R Whurr

Marc Pons Perez

Faidon Mitzalis

Philip A Curnock

Dominic A Waldron

A turbofan engine has: an engine core producing a core exhaust flow; an upstream fan; a bypass duct carrying a bypass air flow produced by the fan; an exhaust assembly. The turbofan engine afterburner system has: a core plug; second core flow duct, and entrance(s) from the first core flow duct for diversion into the second of a portion of the core exhaust flow, and exit for re-joining the diverted portion of the core exhaust flow to the undiverted portion of the core exhaust flow; door(s) open during normal operation of the engine but closable, during a reheat operation, to block the entrances to the second core flow duct; and fuel injector(s) and igniter(s) operable, during the reheat operation, to inject and ignite fuel within the second core flow duct, providing a reheat flow into the core exhaust flow from the exit of the second core flow duct.

Afterburner system for turbofan engine

A gas turbine engine () comprising a rear cowl () defining an exhaust aperture () and a motive system. The rear cowl () comprises at least one panel () and the motive system is operable to selectively move the panel () between deployed and stowed configurations by rotation of the panel () about an axis substantially parallel to the main rotational axis of the engine (). This alters the area of the exhaust aperture ().

Gas turbine cowl

A turbine engine includes an engine core bounded by a bypass duct, a first portion of the bypass duct defined by a fan casing having a radially inner wall and a radially outer wall, a second portion of the bypass duct defined by a radially inner wall and a radially outer wall, a third portion of the bypass duct provided as at least one access door comprising a flow guide structure; and a thrust reverser mechanism coupled to the fan casing.

Turbine engine with access door to engine core

A mounting assembly for attaching a ducted fan gas turbine engine that includes an intake, a propulsive fan, a fan case surrounding the fan, and a core engine. The air intake is attached to the front of the fan case such that loads acting on the air intake are transmitted to the fan case. The mounting assembly includes: a support structure extending in an axial direction of the engine and having a rearward region adapted to attach to the aircraft; and a load distribution ring coaxial with and rearward of the fan case, adapted to join to the fan case, and joined to a forward region of the support structure. The support structure and the load distribution ring are adapted such that the primary load path for the loads transmitted to the fan case by the air intake is through the load distribution ring and the support structure.

Mounting assembly

A ducted fan gas turbine assembly has a propulsive fan driven by a core engine. The turbine assembly has an annular bypass duct which receives an airflow from the fan and is bounded on the radially inward side by the core engine and on the radially outward side by an engine nacelle. The turbine assembly has a thrust reverser assembly having a vane arrangement including a first set of turning vanes for channelling airflow from the duct in a rearward direction, a second set of turning vanes for channelling airflow from the bypass duct in a forward direction. The thrust reverser assembly includes a plurality of blocker doors which are deployable to block the bypass duct. The nacelle has stationary and movable cowl portions that cooperate with the thrust reverser assembly to provide several operational configurations.

Ducted fan gas turbine assembly

A mounting arrangement of a gas turbine engine comprising a core engine, surrounded by a nacelle having a bypass duct, the mounting arrangement comprising a front mount, a rear mount and characterized by the mounting arrangement further comprising a fail-safe mount axially spaced from the front and rear mounts. The fail-safe mount comprises a number of A-frames connecting the core engine and the bypass duct. In normal operation the fail-safe mount does not transmit loads between the engine and a pylon, except in the event of damage to either the front or rear mounts.

Aeroengine mounting

A turbine engine arrangement includes an electrical machine that acts as a generator or motor. During initial start-up, the electrical machine acts as the motor to drive shaft rotation. The arrangement includes a compressor fan that generates an airflow utilized by an air turbine to drive the electrical machine as a generator. A duct directs airflow exhausted from the air turbine to a heat exchanger to exchange heat with a bypass flow from the compressor fan. In such circumstances, the generator can operate substantially independently of a rotational speed of the engine shafts within the core, whilst bled air through the valve acts to cool the electrical machine during initial start-up. A gearbox is provided for matching air turbine rotation with generator requirements whilst also allowing for connection to the primary drive shaft of the core to allow engine start-up or driving of the generator.

Turbine engine arrangement

A gas turbine engine comprising a bypass duct defined radially outwardly by a nacelle and radially inwardly by a core engine casing. The nacelle comprises a thrust reverser unit having at least one blocker door rotatably attached to a static part and slidably connected to a translating part. The translating part is arranged to move between a stowed position and a deployed position and in the deployed position the blocker door spans the bypass duct. In the stowed position the blocker door is stowed inside the translating part and does not form part of an airwash surface of the bypass duct.

Aeroengine thrust reverser

A gas turbine engine comprising a core engine a fan and a fan casing surrounding the fan and extending rearwardly to attach to an array of outlet guide vanes characterised in that a cascade is rigidly attached to the fan casing and is connected to the core engine via a second support.

A turbine engine arrangement incorporates an electrical machine combination which can act as a generator or motor. Thus, the combination during initial turbine engine arrangement start-up acts through this motor to drive shaft rotation. This shaft rotation creates core compressed air which is bled through a valve to an air turbine such that the electrical machine when acting as a motor or generator at low engine loads is appropriately cooled. The arrangement also includes a compressor fan which generates an airflow utilised by the air turbine in order to drive the electrical machine as a generator of electrical power when engine conditions dictate. A duct is provided to direct airflow exhausted from the air turbine to a heat exchanger arranged to exchange heat with a bypass flow from the compressor fan. In such circumstances, the generators can operate substantially independently of rotational speed of the engine shafts within the core whilst bled air through the valve acts to cool the electric machine during initial start-up. Generally, a gearbox is provided whereby matching of air turbine rotation with generator requirements is achieved whilst also through a coupling allowing connection to the primary drive shaft of the core to either allow engine start-up or driving of the generators when engine speed is appropriate.

A mounting system for use in mounting a gas turbine engine having an engine core to an aircraft comprises an engine support arrangement and front and rear mounting assemblies to mount the engine support arrangement to a casing surrounding the engine core. Each of the front and rear mounting assemblies comprises a plurality of circumferentially spaced mounting members to effect the aforesaid mounting of the engine support arrangement to the casing.

Mounting system for use in mounting a gas turbine engine

A gas turbine engine comprising a nacelle having an intake, the intake defining a generally annular chamber, an engine accessory and a heat exchanger for cooling a fluid of the accessory. The chamber is closed and the heat exchanger is disposed within the chamber operable to provide heat to prevent ice forming on the intake during engine operation.

Aeroengine intake having a heat exchanger within an annular closed chamber

A mounting assembly () for mounting a gas turbine engine on an aircraft. The assembly () comprising four equispaced hydraulic piston and cylinder thrust links () connecting between the engine fan case () and the air intake (), which intake () is mounted to the airframe.

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Derby, United Kingdom

Peter Kevin Beardsley