Rolls-royce Corporation

Matthew S Cartwright

David Reginald Trainer

Mark Sweet

Michael Yeandel

A gas turbine engine includes: first spool including first compressor and first turbine drivingly coupled by first main shaft; second spool including a second compressor and second turbine drivingly coupled by second main shaft; combustion equipment; electrical machine arrangement including: first rotor drivingly coupled to first main shaft and carrying array of rotor elements; second rotor drivingly coupled to second main shaft and carrying array of rotor elements; and stator arrangement including array of stator coils arranged around an axis, axis being coaxial with an axis of rotation of first rotor and an axis of rotation of second rotor. Stator arrangement is axially translatable relative to first and second rotors, between: a first axial position in which array of stator coils interacts with array of rotor elements of first rotor; and a second axial position in which array of stator coils interacts with array of rotor elements of second rotor.

Gas turbine engine

Aircraft power and propulsion systems and methods thereof; an aircraft power and propulsion system includes: a gas turbine engine having first and second spools; one or more electrical networks; a first electrical machine joined with the first spool; a second electrical machine joined with the second spool; a first power converter having first and second sides; a second power converter having first and second sides; and a controllable switching arrangement in which a connection to the first side of the second power converter is switchable between: a winding of the second electrical machine, or the winding of the first electrical machine.

Electrically starting a gas turbine engine

Disclosed is an aircraft accessory drive system comprising: a drive shaft configured to provide a drive input; a critical accessory directly coupled to the drive shaft so as to be directly driven by the drive shaft; a parasitic drive system configured to transmit drive input from the drive shaft to one or more less critical accessories, wherein the parasitic drive system comprises a torque limiter configured to decouple the parasitic drive system from the drive shaft and the critical accessory in response to a jam affecting the parasitic drive system or one or more of the less critical accessories. Also disclosed are a gas turbine engine comprising an aircraft accessory drive system, and an aircraft comprising an aircraft accessory drive system.

Aircraft accessory drive system

A method of operating an aircraft electrical power distribution system comprises determining a measure of ambient pressure; and setting a target operating voltage in accordance with the measure of ambient pressure. The method further comprises controlling the operating voltage in accordance with the set target operating voltage. The target operating voltage may refer to a distribution voltage of the aircraft. An aircraft electrical power distribution system is also disclosed, comprising: a sensor configured to determine a measure of ambient pressure; a controller configured to set a target operating voltage in accordance with the measure of ambient pressure, and a voltage regulator configured to regulate the operating voltage in accordance with the set target value.

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Derby, United Kingdom

Matthew S Cartwright