Rolls-royce Corporation

Rolls-royce Deutschland Ltd & Co. Kg

David Edwards

Clare Lindsay Bewick

David Stephen Williams

Stephan Uhkoetter

Neil J Davies

Cristina Diaz Garcia

Sebastian Ray

William A Malewicz

Samuel W White

John R Mason

Stefan Menczykalski

Lynn Hammond

Alan Robert Maguire

David Peter Scothern

Martyn Richards

Glenn A Knight

Stewart T Thornton

John Gebhard

Gervas Franceschini

Stephan Uhkötter

Adam L Kempers

Jeremy Gallagher

David C Butt

Geoffrey E Kirk

Isabelle Erickson

Adam Kempers

Stewart Thornton

David Williams

An oil delivery system is provided that includes a tank for a gas turbine engine, where the tank is positioned radially outward from a compressor section, a combustor section, and/or a turbine section of the gas turbine engine. The tank is configured to store oil for the gas turbine engine. The oil delivery system further includes a primary lubrication system including a sump of a power gearbox, a pump, and an oil feed line. The oil feed line extends from the tank to the primary lubrication system. The oil feed line is configured to allow a flow of oil to pass from the tank to the pump and from the pump through the power gearbox to the sump of the power gearbox.

Oil tank for geared turbofan engine

An oil tank filling system for filling the oil tank of a gas turbine engine that includes an aft core cowl. The system includes an oil tank that has an oil tank top and an oil tank bottom and is located within a core of the engine, an oil access port located on the aft core cowl, and an oil tank filling pipe that leads from the oil access port to a tank filling port located at or adjacent the oil tank bottom. The system is configured so that oil that is supplied to the oil access port flows to and into the oil tank using gravitational force. A method of filling the oil tank of a gas turbine engine and a gas turbine engine that includes the oil tank filling system.

Oil tank filling system

A gas turbine engine for an aircraft including a unit supplied with oil from a first oil circuit and a second oil circuit. The first oil circuit and the second oil circuit each are fluidly coupled with at least one inlet and with at least one outlet of the unit and with at least one inlet and with at least one outlet of an oil tank. The first oil circuit and the second oil circuit are configured to receive oil from the oil tank and to direct the received oil to the unit. The oil tank is incorporating offset outlets to each of the oil circuits. The offset outlet of the second oil circuit is positioned higher in the oil tank than the offset outlet of the first oil circuit.

Gas turbine engine

The disclosure relates to a gas turbine engine having an accessory gearbox assembly having an accessory gearbox. The accessory gearbox assembly is mounted adjacent a core of the gas turbine engine and has a support formation for supporting a conduit. The conduit extends between a first location on the engine and a second location on the engine. The first location and the second location may be spaced from the accessory gearbox such that the conduit does not operatively communicate with the accessory gearbox in use. The accessory gearbox may be axially mounted and may provide a bridge for supporting a plurality of conduits.

Accessory gearbox assembly

An oil tank filling system for filling the oil tank of a gas turbine engine. The system includes an oil tank located within a core of the engine, an oil filling reservoir located within a bifurcation that extends from the core of the engine, an oil tank filling pipe that leads from the oil filling reservoir to a tank filling port on the oil tank, and an oil pump. The system is configured so that the oil pump pumps oil from the oil filling reservoir through the oil tank filling pipe and the tank filling port to fill the oil tank. A method of filling the oil tank of a gas turbine engine and a gas turbine engine that includes the oil tank filling system are also disclosed.

A gas turbine engine includes a gearbox receiving input from a core shaft and driving a fan at a lower speed than the core shaft. First and second oil circuits fluidly couple with an inlet and outlet of the gearbox. A third oil circuit fluidly couples with an inlet and outlet of the gearbox. The outlet of the gearbox includes a device directing oil from the gearbox to the first oil circuit, to the second oil circuit and to the third oil circuit when feeding to the gearbox exceeds a predefined oil flow rate, or deviates an operational value corresponding with that oil flow rate, and directs oil from the gearbox to the third oil circuit when feeding to the gearbox is &#x2264; the predefined flow rate or is &#x2264; a corresponding operational value or is greater than or equal to a further corresponding operational value.

An auxiliary oil supply apparatus for a rotating device (), the rotating device comprising a primary oil supply (), a rotating component () and a static component () situated radially outwardly of a centre of rotation of the rotating component () and arranged to collect oil () held radially outwardly from the rotating component () as the rotating component rotates. The auxiliary oil apparatus comprises a scoop () associated with the rotating component () and is responsive to a change in a known parameter to move between a first position in the static component () to a second position between the static component () and the centre of rotation.

Auxiliary oil supply apparatus for a rotating component

A tank assembly () for a gas turbine engine is provided comprising a tank () and a plurality of restraints (). The restraints () include a fixing part () for securing the tank () to a support structure (). A first restraint () has a first rigidity in the direction of a length of the tank () and at least one second restraint () has a second rigidity in the direction of the length of the tank (). Upon thermal expansion or contraction of the tank () relative to the support structure (), the or each second restraint () flexes to a greater extent than the first restraint ().

Tank assembly

An oil tank filling system for filling the oil tank of a gas turbine engine that includes an aft core cowl. The system includes: an oil tank that is located within a core of the engine; an oil access port located on the aft core cowl; an oil tank filling pipe that connects the oil access port to a tank filling port on the oil tank; and a hydraulic lock that prevents oil entering the oil tank once the oil tank contains a predetermined volume of oil. A method of filling the oil tank of a gas turbine engine and a gas turbine engine that includes the oil tank filling system are also disclosed.

A thrust balancing mechanism for balancing axial loads on a rotor thrust bearingis described. The mechanism comprises a piston arrangementaxially mounted on a stationary structure, about a center axis arranged, in use, in coaxial alignment with a rotating shaftcarrying the rotor thrust bearing. A hydrodynamic thrust bearingis mounted, in use, between the pistonand the rotor thrust bearing. The pistonis pressurized so as to impart to the rotor thrust bearing, via the hydrodynamic thrust bearing, an axial load which counters an axial load imparted to the rotor thrust bearingby the rotating shaft

Balancing of axial thrust forces within a gas turbine engine

A leaf seal is proposed for effecting a seal between two coaxial and relatively rotating components. The seal has an annular pack of stacked leaves, the pack being mountable to a first one of the components at root portions of the leaves and extending towards the other component such that end edges of the leaves cooperate to define a seal surface of the pack which is presented for air-riding interaction with a surface of the other component during relative rotation between the components such that, in use, a pressure drop is maintained axially across the pack. The seal surface of the pack incorporates a plurality of hydrodynamic lift-generating recesses spaced circumferentially around the pack. Each said recess extends circumferentially across a plurality of adjacent leaves in the pack, each of which leaves being spaced radially from said surface of the other component along at least part of its end edge.

Leaf seal

A propulsion engine for an aircraft includes a first fan having a set of first blades and a second fan having a set of second blades. There is provided a first angular pitch adjustment mechanism coupled to the first set of blades, a second angular pitch adjustment mechanism coupled to the second set of blades and an actuation device coupled to the first angular pitch adjustment mechanism. The first and second angular pitch adjustment mechanisms are coupled together such that when the actuation device generates an output, the angular pitch of each of the first blades and each of the second blades changes.

Propulsion engine

A power transmission arrangement comprises a first power transmission member connectable to a first main shaft of an engine. The arrangement also includes a second power transmission member connectable to a second main shaft of the engine and to a third power transmission member. A coupling assembly is provided which has a selectable coupling condition to couple the first power transmission member to the second power transmission member to allow power to be transmitted from the third power transmission member to the first main shaft of the engine via the first power transmission member. The coupling assembly has a decoupling condition to decouple the first power transmission member from the second power transmission member to allow power to be transmitted from the main shaft of the engine to the third power transmission member via the second power transmission member.

Growing community of inventors

Derby, United Kingdom

David Edwards