Rolls-Royce Corporation

Rolls-Royce Deutschland Ltd & Co. Kg

Neil J Davies

David Edwards

David Stephen Williams

John R Mason

Stefan Menczykalski

Alan Robert Maguire

Stephan Uhkötter

Stephan Uhkoetter

Lynn Hammond

Richard Sharpe

David Williams

A system for supplying lubricant to a component of a gas turbine engine is provided. The system includes a first fluid circuit having a first pump drivably couplable to a fan shaft of the engine for pumping a lubricant from a lubricant tank to the component. The first fluid circuit allows only a unidirectional flow of the lubricant from the lubricant tank to the component via the first pump. The system also includes a second fluid circuit having a second pump drivably couplable to the fan shaft for pumping the lubricant from the component to the lubricant tank. The second fluid circuit allows only a unidirectional flow of the lubricant from the component to the lubricant tank via the second pump. First and second ports of the two pumps operate as input ports or output ports depending on the rotation direction of the fan shaft.

Gas turbine engine lubrication system

A system for supplying lubricant to a component of a gas turbine engine having a fan shaft is provided. The system includes a pump drivably couplable to the fan shaft for pumping lubricant to the component. The pump includes an inlet for receiving lubricant from a lubricant source, an outlet for outputting lubricant to the component and a swashplate movable between at least a first position and a second position. The system also includes a swashplate actuator for actuating the swashplate between the first position and the second position according to whether the fan shaft is rotating in a forward direction or a reverse direction opposite to the forward direction.

System for supplying lubricant to a component

An oil scavenge system for a gas turbine engine comprising an oil tank and at least one bearing chamber. The oil scavenge system comprises at least one primary scavenge pump, a manifold, a secondary scavenge pump, a deaerator and a filter unit. The at least one primary scavenge pump is configured to pump oil from the at least one bearing chamber to the manifold whilst raising the pressure of the oil from a starting pressure to a first pressure elevated with respect to the starting pressure. The manifold is pressurised to substantially maintain the oil at said first pressure. The secondary scavenge pump is configured to pump oil from the manifold at the first pressure and to raise the pressure of the oil to a second pressure elevated with respect to the first pressure before pumping the oil to the deaerator and through the filter unit to the oil tank.

Oil scavenge system

A lubrication system for a gas turbine engine, the system comprising: a gearbox, the gearbox comprising a sump; an oil tank; a primary gearbox lubrication system configured to pump oil from the oil tank to lubricate the gearbox with a gearbox primary feed; a secondary gearbox lubrication system, configured to lubricate the gearbox with oil from the sump when the oil level in the sump reaches a predetermined level; wherein the system is configured to increase the oil level in the sump to at least the predetermined level in response to a failure of the primary gearbox lubrication system.

Lubrication 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

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.

Growing community of inventors

Ashbourne, United Kingdom

Neil J Davies