Rolls-royce Corporation

Malcolm L Hillel

Peter Swann

Paul Fletcher

Nicholas Howarth

Huw Llewelyn Edwards

Robert John Miller

James Vincent Taylor

Bryce D Conduit

Christopher R Hall

Anthony M Dickens

Rory Douglas Stieger

Andrew Martin Rolt

Alexis Lambourne

Stephen Geoffrey Brown

Sean Patrick Ellis

Thierry Moes

Alasdair Gardner

Jae-Hoon Chung

Christopher Clay

Parag Vyas

A system for capture of atmospheric carbon dioxide. The system includes a carbon dioxide capture device having a capture medium operable to capture atmospheric carbon dioxide under a first set of thermodynamic conditions, and to release carbon dioxide under a second set of thermodynamic conditions different to the first set of thermodynamic conditions. The first set of thermodynamic conditions includes a first temperature range and the second set of thermodynamic conditions includes a second temperature range. A heat engine is configured receive a working fluid at an inlet temperature and arranged to discharge at least a portion of the working fluid at a discharge temperature in the second temperature range or higher, and a heat transfer arrangement is configured to convey heat from discharged working fluid to the capture medium to release carbon dioxide therefrom.

Carbon dioxide capture

A computer-implemented method comprising: controlling input of data quantifying damage received by a compressor of a gas turbine engine into a first machine learning algorithm; receiving data quantifying a first operating parameter of the compressor as an output of the first machine learning algorithm; and determining operability of the compressor by comparing the received data quantifying the first operating parameter of the compressor with a threshold.

Computer-implemented methods for determining compressor operability

An aircraft comprises a hydrogen-fuelled propulsion system, a plurality of like generally cylindrical hydrogen storage tanks and a conveying system arranged to convey hydrogen from the hydrogen storage tanks to the hydrogen-fuelled propulsion system. The aircraft further comprises a fuselage having a cargo bay () including one or more (A-G) of the plurality of hydrogen storage tanks, the longitudinal axes (A-G) of the one or more hydrogen storage tanks within the cargo bay extending parallel to the longitudinal axis () of the fuselage and lying in one or more planes () extending across the width dimension of the cargo bay. The hydrogen storage tanks within the cargo bay have a common aspect ratio R in the range 4.2≤R≤25.7, allowing the volume of space with the cargo bay occupied by stored hydrogen to be maximised or approximately maximised.

Aircraft comprising hydrogen storage tanks

A computer-implemented method controls input of at least a portion of a first training data set into a first machine learning algorithm. The first training data set includes data quantifying damage to a first compressor and data quantifying a first operating parameter of the first compressor. The first machine learning algorithm is executed, and data quantifying the first operating parameter is received as an output of the first machine learning algorithm. The first machine learning algorithm is trained using the received data output from the first machine learning algorithm and data quantifying the first operating parameter of the first compressor. The trained first machine learning algorithm is configured to enable determination of operability of a second compressor of a gas turbine engine.

Computer-implemented methods for training a machine learning algorithm

A bladed disk may be arranged to rotate about an axis of rotation and including a rotor disk having an axial length extending from a first end to a second end, along the axis of rotation and a radial thickness extending between a first radius from the axis of rotation and a second radius from the axis of rotation, less than the first radius. The bladed disk may include a plurality of blades formed integrally with the rotor disk and arranged circumferentially around the rotor disk, and a first set of divides and a second set of divides, each divide comprising a partial break in the rotor disk extending axially from the first end of the rotor disk to the second end of the rotor disk and radially from the first radius to a third radius, less than the first radius and greater than the second radius.

Bladed disk

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

The invention concerns an aircraft propulsion control system in which a gas turbine engine has an actuable flow opening for control of flow to or from a portion of the engine. One or more sensor is arranged to sense a condition indicative of vapor trail formation by the exhaust flow from the engine. A controller is arranged to control actuation of the flow opening so as to reduce the efficiency of the engine upon sensing of said condition by the one or more sensor. In one example, the flow opening is a variable area fan nozzle.

Aircraft vapour trail control system

A turbofan gas turbine engine () comprises a variable area exhaust nozzle () arranged at the downstream end of a casing (). A control unit () analyzes the power produced by the gas turbine engine (), the flight speed of the gas turbine engine () and/or the altitude of the gas turbine engine (). The control unit () configures the variable area nozzle () at a first cross-sectional area (A) when the flight speed of the gas turbine engine () is less than a first predetermined value. The control unit () configures the variable area nozzle () at a second, smaller, cross-sectional area (B) when the flight speed of the gas turbine engine () is greater than the first predetermined value and the power produced by the gas turbine engine () is greater than a second predetermined value. The control unit () configures the variable area nozzle () at a third, intermediate, cross-sectional area (C) when the flight speed of the gas turbine engine () is greater than the first predetermined value and the power produced by the gas turbine engine () is less than the second predetermined value.

Growing community of inventors

Derby, United Kingdom

Malcolm L Hillel