Rolls-royce Corporation

Clare Lindsay Bewick

Richard Peace

David Edwards

William A Malewicz

Cristina Diaz Garcia

Samuel W White

Sebastian Ray

Lucian Ingley

Roberts Goulds

Gawain Charles Raydon Badcock

A gas turbine engine for an aircraft is provided. The gas turbine engine comprises an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor. The gas turbine engine further comprises a fan located upstream of the engine core, the fan comprising a plurality of fan blades, the fan generating a core airflow which enters the engine core and a bypass airflow which flows through a bypass duct surrounding the engine core. The gas turbine engine further comprises a circumferential row of outer guide vanes located in the bypass duct rearwards of the fan, the outer guide vanes extending radially outwardly from an inner ring which defines a radially inner surface of the bypass duct.

Gas turbine engine inner barrel

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

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 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 method for detecting a fault in a gas supply system for a gas turbine engine. The method comprises: measuring a pressure difference between two gas supplying ducts of the gas supply system; comparing the measured pressure difference to a threshold level; and determining a fault based on the measured pressure difference and the comparison.

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Derby, United Kingdom

Clare Lindsay Bewick