Rolls-royce Corporation

Rolls-royce Deutschland Ltd & Co. Kg

John R Mason

David Edwards

Stephan Uhkötter

David Stephen Williams

Stephan Uhkoetter

Neil J Davies

Stefan Menczykalski

Lynn Hammond

David Brown

Thomas Philip Astley

Keith Whittingham

David Williams

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

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.

A method () and apparatus () for lubrication of a gearbox () of an aircraft engine comprise provision () of oil to the gearbox () through a primary oil system () driven by a core () of the engine () in normal conditions; detection () of windmilling conditions and/or failure of the primary oil system (); and in response to the detected condition or failure, activation () of an electric pump () of an auxiliary oil system (), to provide oil to the gearbox ().

Oil system

A turbine arrangement for a gas turbine engine comprising a turbine shaft. An axial array of turbine rotors, having a first axial end and a second axial end. A drive arm coupled between the turbine shaft and the first axial end. A measurement system arranged to measure a parameter of the turbine arrangement, the measurement system positioned at the second axial end. The parameter may be rotational speed.

Turbine arrangement

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Bristol, United Kingdom

John R Mason