Rolls-Royce Corporation

Rolls-Royce Deutschland Ltd & Co. Kg

Rory Douglas Stieger

Daniel Swain

Mark David Taylor

Marko Bacic

Matthew Moxon

Ian J Bousfield

Benjamin J Sellers

Malcolm L Hillel

Kevin M Britchford

Lorenzo Raffaelli

Mikko Mattila

Ivan Popovic

Michael O Hales

Sean Patrick Ellis

Erik Janke

Conor Hickey

Thierry Moes

John Coupland

Alexander George Wilson

Nigel Smith

Paul J R Strange

Roy S Bartle

Parag Vyas

Malcolm Laurence Hillel

Nicholas Cristinacce

Roy Bartle

An auxiliary power unit () for an aircraft () comprises a gas turbine engine comprising an engine core (). The engine core comprises a core compressor () and core turbine () coupled by a core shaft (). The auxiliary power unit further comprises a load spool comprising a load compressor (), a load turbine () and a permanent magnet electric machine (), each being coupled by a load shaft (). The load shaft () and core shaft () are configured to rotate independently of one another.

Aircraft auxiliary power unit

A gas turbine engine including: a high pressure turbine, a low pressure turbine, a high pressure compressor coupled to the high pressure turbine by a high pressure shaft, a propulsor and a low pressure compressor coupled to the low pressure turbine via a low pressure shaft and a reduction gearbox; wherein the high pressure compressor defines an average stage pressure ratio at cruise conditions of between 1.25 and 1.35 and consists of 10 or 11 stages; and the high pressure compressor and low pressure compressor together define a core overall pressure ratio at cruise conditions of between 40:1 and 60:1.

High pressure ratio gas turbine engine

A gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The gas-generator compressor is an axi-centrifugal compressor comprising a plurality of axial compression stages followed by a single centrifugal compression stage, wherein the International Standard Atmosphere, sea-level static (hereinafter ISA SLS) design point pressure ratio of the axi-centrifugal compressor is from 12 to 16, and a ratio of the ISA SLS pressure rise across the axial compression stages to the ISA SLS pressure rise across the centrifugal compression stage is from 0.75 to 1.

Gas turbine engine

A turboshaft gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The expansion ratios of the turbines are dependent upon an outlet temperature of the combustor, and an expansion relationship between the turbines is defined as the ratio of expansion ratios of the turbines over a running range of non-dimensional power outputs of the gas turbine engine. A second derivative of the expansion relationship is from 0.6 to 1.0.

Turboshaft gas turbine engine and expansion ratio relationship

A turbofan engine has an engine core including in flow series a compressor, a combustor and a turbine. The engine further has a fan located upstream of the engine core, has a supersonic intake for slowing down incoming air to subsonic velocities at an inlet to the fan formed by the intake, has a bypass duct surrounding the engine core, wherein the fan generates a core airflow to the engine core and a bypass airflow through the bypass duct, and has a mixer for mixing an exhaust gas flow exiting the engine core and bypass airflow exiting bypass duct. The engine further has a thrust nozzle rearwards of the mixer for discharging mixed flows, the thrust nozzle having a variable area throat. The engine further has a controller controlling the thrust produced by the engine over a range of flight operations including on-the-ground subsonic take-off and subsequent off-the-ground subsonic climb.

Supersonic aircraft turbofan

Electrical machine apparatus comprising: a rotor having a longitudinal axis and being arranged to rotate about the longitudinal axis in a first circumferential direction, the rotor defining one or more conduits for receiving fluid therein, the one or more conduits including an inlet and an outlet; and a fluid guide defining a first aperture arranged to direct fluid in a second direction towards the rotor, the second direction having a positive circumferential component in the first circumferential direction.

Electrical machine apparatus

Electrical machine apparatus comprising: a rotor having an axis of rotation and defining a cavity therein; and a conduit positioned within the cavity of the rotor, the conduit comprising an inlet arranged to receive a fluid and an outlet arranged to exhaust the fluid, the inlet having a first radial distance from the axis of rotation and the outlet having a second radial distance from the axis of rotation, the first radial distance being greater than the second radial distance.

Electrical machine apparatus having a conduit with a particular arrangement for an inlet and outlet

An electrical machine has a stator carrying electrical windings which protrude at opposite ends of the stator to form respective, ring-shaped end windings. The electrical machine further has a rotor having a plurality of magnetic field-producing elements for producing a rotor magnetic field which interacts with a stator magnetic field produced by the windings. The electrical machine further has a coolant bath for holding liquid coolant. The electrical machine further has a heat sink in thermal contact with at least one of the end windings, the bath and the heat sink being configured such that the heat sink is immersed in the coolant held in the bath. The heat sink defines one or more fluid pathways configured such that vapour bubbles, formed when coolant in contact with the heat sink boils, escape by rising through the heat sink.

Electrical machine

A control system for use in controlling a cabin blower system. The cabin blower system includes a gas turbine engine spool, a cabin blower compressor powered by the spool and arranged in use to compress fluid used in a cabin of an aircraft, and one or more control mechanisms via which the control system controls the power extracted by the cabin blower compressor from the spool. The control system is arranged in use to control the power extracted from the spool by the cabin blower compressor in accordance with one or more primary control parameters. The control system is arranged in use to alter the spool power extracted by the cabin blower compressor by comparison with the power that would have been extracted in accordance with the primary control parameters alone, in response to modifications in a secondary control parameter indicative of the commencement or occurrence of an engine transient.

Control system for a cabin blower system

An aircraft pneumatic system includes a main gas turbine engine including a main compressor, a recuperated auxiliary gas turbine engine including a core compressor having an inlet in fluid communication with a main compressor bleed of the main gas turbine engine and an environmental control system inlet in fluid communication with the main compressor bleed of the main gas turbine engine. The environmental control system includes a compressor driveable by power provided by the auxiliary gas turbine engine.

Aircraft pneumatic system

An aircraft () comprising a fuselage (), the fuselage () comprising at least first and second inwardly tapering portions () extending in a generally rearward direction from an aft end of the fuselage (), each inwardly tapering portion () comprising a boundary layer ingesting propulsor () mounted thereon.

Aircraft

An air duct arrangement () for an aircraft (). The arrangement () comprises an environmental control system (ECS) (). The ECS () comprises an air inlet () arranged to ingest a low velocity portion of a boundary layer flow adjacent the aircraft fuselage (), and to deliver a flow of air to an environmental control system air intake (). The arrangement () further comprises an ejector () arranged to receive an ECS exhaust (), and boundary layer air from an aft region of the aircraft (), and to exhaust air to the ambient airstream at an aft portion of the aircraft ().

Aircraft environmental control system air duct arrangement

A method of operating a gas turbine engine compressor. The method includes: determining an operating point of the compressor, and modulating mass flow of environmental control system input air to maintain the operating point of the gas turbine engine compressor within predetermined limits.

Method and apparatus for controlling a compressor of a gas turbine engine

A method of controlling an aircraft gas turbine engine cooling system. The cooling system includes a heat exchanger having a first fluid path through which fan air flows, and a second fluid path through which relatively hot compressor air flows. The cooling system includes a valve configurable between an open position corresponding to a first operating mode, where fan air flows through the first path cooling the compressor air in the second path to a lower temperature, and a closed position corresponding to a second operating mode, where fan air may flow through the first path at a reduced rate, thus the compressor air in the second path could be cooled to a lesser extent. The valve is operated in first mode when the aircraft is in a descent mode, or when turbine entry temperature is above a predetermined amount. Otherwise, the valve is operated in second mode.

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Derby, United Kingdom

Rory Douglas Stieger