公开(公告)号：US10308353B2

公开(公告)日：2019-06-04

申请号：US15097975

申请日：2016-04-13

Applicant: ROLLS-ROYCE plc

Inventor： Peter Swann

IPC: B64C25/40 ,  B64C25/34 ,  B64C25/46 ,  B64D41/00 ,  B64C25/42

Abstract: Apparatus for controlling velocity of aircraft during landing roll-out and/or taxiing, the apparatus comprising: a generator for absorbing kinetic energy from a landing gear of the aircraft to generate electrical energy; and a component of the aircraft for receiving and consuming electrical energy from the generator, the generator and the component being electrically connected to one another without an intervening electrical energy storage device.

公开(公告)号：US10116141B2

公开(公告)日：2018-10-30

申请号：US14942104

申请日：2015-11-16

Applicant: ROLLS-ROYCE PLC

Inventor： Peter Swann ,  Armin Stranjak

IPC: H02J3/46 ,  G05B15/02 ,  G06Q50/06 ,  H02J3/38

Abstract: This invention concerns a method and apparatus for coordinating energy distribution over a local energy network having at least one generator and a plurality of systems requiring an energy supply for operation, each system in the local network being connected to the at least one generator and/or another system in the network for distribution of energy there-between. An agent for each respective one of the generator and systems has a data store, a data processor and a data transmitter and receiver for transmission and receipt of data communication with one or more of the other agents. The data processor of each agent is programmed to recognize a predetermined communication sequence having a plurality of ordered data communication steps required to initiate supply of energy between the generator or system of said agent and the generator or system associated with another agent. Each communication sequence is assigned a future time period for which the energy supply is to be enacted.

公开(公告)号：US12152497B2

公开(公告)日：2024-11-26

申请号：US18328225

申请日：2023-06-02

Applicant: ROLLS-ROYCE plc

Inventor： Peter Swann ,  David M Beaven ,  Craig W Bemment ,  Alastair G Hobday ,  Benjamin J Keeler ,  Christopher P Madden ,  Martin K Yates

IPC: F01D21/00 ,  F02C9/28

Abstract: A method of determining one or more fuel characteristic of an aviation fuel suitable for powering a gas turbine engine of an aircraft is disclosed. The method includes: determining, during use of the gas turbine engine, one or more contrail parameters related to contrail formation by the gas turbine engine. The determining of the one or more contrail parameters includes performing a sensor measurement on a region behind the gas turbine engine in which a contrail is or can be formed. The method also includes determining one or more fuel characteristics of the fuel based on the one or more contrail parameters. A fuel characteristic determination system, a method of operating an aircraft and an aircraft are also disclosed.

公开(公告)号：US20240301829A1

公开(公告)日：2024-09-12

申请号：US18663599

申请日：2024-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Craig W BEMMENT ,  Benjamin J. Keeler ,  Christopher P. Madden ,  Andrea Minelli ,  Peter Swann ,  Martin K. Yates

IPC: F02C7/14 ,  F02C7/06 ,  F02C7/10 ,  F02C7/224 ,  F02C7/36

CPC classification number: F02C7/14 ,  F02C7/06 ,  F02C7/10 ,  F02C7/224 ,  F02C7/36 ,  F05D2220/323 ,  F05D2260/205 ,  F05D2260/213 ,  F05D2260/98

Abstract: A gas turbine engine includes an engine core with a combustor; a turbine including turbine blades; a compressor as a source of cooling air for the turbine blades; and an inducer to accelerate and direct the cooling air onto the turbine blades, and a modulating valve to allow or block cooling air flow into a subset of airflow passageways of the inducer; and a fuel management system to provide fuel to the combustor. The fuel management system includes a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger through which oil and the fuel flow, to transfer heat between the oil and the fuel. A method of operating the engine includes using the modulating valve to adjust the cooling air flow based on turbine inlet temperature; and transferring 200-600 kJ/m3 of heat to the fuel from the oil in the primary fuel-oil heat exchanger at cruise conditions.

公开(公告)号：US11994072B1

公开(公告)日：2024-05-28

申请号：US18337559

申请日：2023-06-20

Applicant: ROLLS-ROYCE PLC

Inventor： Craig W Bemment ,  Benjamin J Keeler ,  Christopher P Madden ,  Andrea Minelli ,  Peter Swann ,  Martin K Yates

IPC: F02C7/224 ,  F02C7/14 ,  F02C7/18 ,  F02C7/232 ,  F02C9/28

CPC classification number: F02C7/224 ,  F02C7/14 ,  F02C7/18 ,  F02C7/232 ,  F02C9/28 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2270/303

Abstract: A method of operating a gas turbine engine is disclosed, the gas turbine engine comprising an engine core comprising a combustor arranged to burn a fuel; a turbine, the turbine comprising a plurality of turbine blades; a compressor arranged to be used as a source of cooling air for the turbine blades; and an inducer arranged to accelerate and direct the cooling air onto the turbine blades and comprising a plurality of airflow passageways and a modulating valve arranged to control cooling air flow into a subset of the passageways; and a fuel management system arranged to provide the fuel to the combustor, the fuel having a sulphur content of less than 30 ppm. The fuel management system comprises two fuel-oil heat exchangers through which oil and the fuel flow. The method comprises using the modulating valve to adjust the cooling air flow based on turbine inlet temperature.

公开(公告)号：US11788477B1

公开(公告)日：2023-10-17

申请号：US17853494

申请日：2022-06-29

Applicant: ROLLS-ROYCE plc

Inventor： Peter Swann ,  Christopher P Madden ,  Craig W Bemment

IPC: F02C9/40 ,  F02C9/28

CPC classification number: F02C9/40 ,  F02C9/28 ,  F05D2220/323 ,  F05D2270/08 ,  F05D2270/306 ,  F05D2270/31 ,  F05D2270/71

Abstract: An aircraft has first and second fuel sources containing fuels with different characteristics, and one or more gas turbine engines powered by the fuels and each having a staged combustion system having pilot and main fuel injectors and being operable in pilot-only and pilot-and-main ranges of operation. The gas turbine engines each have a fuel delivery regulator arranged to control fuel delivery to the pilot and main fuel injectors. The method includes: obtaining a proposed mission description; obtaining nvPM impact parameters for the gas turbine engines, the impact parameters being associated with each operating condition of the proposed mission; calculating an optimised set of one or more fuel characteristics for each flight condition of the proposed flight defined in the flight description based on the nvPM impact parameters; and determining a fuel allocation based on the optimised set of one or more fuel characteristics.

公开(公告)号：US11739700B2

公开(公告)日：2023-08-29

申请号：US17697761

申请日：2022-03-17

Applicant: ROLLS-ROYCE plc

Inventor： Peter Swann ,  Jonathan E Holt

IPC: F02C9/28 ,  A01G15/00 ,  B64D31/00 ,  B64D37/30 ,  F02C3/22 ,  F02C9/40 ,  B64D27/16

CPC classification number: F02C9/28 ,  A01G15/00 ,  B64D27/16 ,  B64D31/00 ,  B64D37/30 ,  F02C3/22 ,  F02C9/40

Abstract: An aircraft propulsion system includes a hydrocarbon fuel store, a hydrogen fuel store, an engine system capable of producing thrust by combusting hydrocarbon fuel and/or combusting or oxidising hydrogen fuel, a conveying system to convey hydrocarbon and hydrogen fuel from the fuel stores to the engine system and a control system to control the respective flow rates of the fuel within the conveying system. The control system adapts the fractions of the total fuel energy flow rate to the engine system represented by the hydrocarbon and hydrogen fuel energy flow rates in order to reduce climate warming impact caused by at least one of carbon dioxide, water vapour and condensation trails and/or increase climate cooling impact caused by condensation trails produced by the aircraft propulsion system compared to a dual-fuel propulsion system in which a reserve of hydrocarbon fuel is entirely combusted before any of a reserve of hydrogen fuel.

公开(公告)号：US11708796B2

公开(公告)日：2023-07-25

申请号：US17853103

申请日：2022-06-29

Applicant: ROLLS-ROYCE plc

Inventor： Peter Swann ,  David M Beaven ,  Craig W Bemment ,  Alastair G Hobday ,  Benjamin J Keeler ,  Christopher P Madden ,  Martin K Yates

IPC: F02C9/00 ,  F02C9/28

CPC classification number: F02C9/28 ,  F05D2260/80 ,  F05D2270/303 ,  F05D2270/304 ,  F05D2270/708 ,  F23N2221/10

Abstract: The present application discloses a method of determining one or more fuel characteristics of an aviation fuel used for powering a gas turbine engine of an aircraft. The method comprises: determining one or more performance parameters of the gas turbine engine during a first time period of operation of the gas turbine engine; and determining one or more fuel characteristics of the fuel based on the one or more performance parameters. A method of operating an aircraft, a fuel characteristic determination system, and an aircraft are also disclosed.

公开(公告)号：US11530652B2

公开(公告)日：2022-12-20

申请号：US17189663

申请日：2021-03-02

Applicant: ROLLS-ROYCE plc

Inventor： Christopher P. Madden ,  Peter Swann

IPC: F02C9/28 ,  F23R3/34 ,  F02C3/30 ,  F02C9/26

Abstract: A gas turbine engine for an aircraft. The gas turbine comprises a combustor, a fuel injection system connected with a source of fuel and configured to inject fuel into the combustor, a water injection system connected with a source of water and which is configured to inject water into the combustor, and a control system. The control system is configured to identify an atmospheric condition; determine a water-fuel ratio for injection into the combustor of the gas turbine engine in response to the atmospheric condition; and control injection of fuel and water by the fuel injection system and the water injection system according to said water-fuel ratio to control an soot emissions caused by combustion of fuel therein.

公开(公告)号：US10435165B2

公开(公告)日：2019-10-08

申请号：US15846994

申请日：2017-12-19

Applicant: ROLLS-ROYCE plc

Inventor： Peter Swann ,  Paul Fletcher ,  Alvise Pellegrini ,  Ashog Kulathasan

IPC: B64D27/24 ,  B64D31/06 ,  F02C9/48 ,  F02K5/00 ,  F02C9/54 ,  B64D27/02 ,  B64D41/00

Abstract: This invention concerns an aircraft propulsion system in which an engine has an engine core comprising a compressor, a combustor and a turbine driven by a flow of combustion products of the combustor. At least one propulsive fan generates a mass flow of air to propel the aircraft. An electrical energy store is provided on board the aircraft. At least one electric motor is arranged to drive the propulsive fan and the engine core compressor. A controller controls the at least one electric motor to mitigate the creation of a contrail caused by the engine combustion products by altering the ratio of the mass flow of air by the propulsive fan to the flow of combustion products of the combustor. The at least one electric motor is controlled so as to selectively drive both the propulsive fan and engine core compressor.