公开(公告)号：US12085029B2

公开(公告)日：2024-09-10

申请号：US18084083

申请日：2022-12-19

Applicant: ROLLS-ROYCE plc

Inventor： Peter Swann ,  Craig W Bemment ,  Alastair G Hobday ,  Benjamin J Keeler ,  Christopher P Madden

IPC: F02C9/40 ,  F01D21/00 ,  F02C9/28

CPC classification number: F02C9/40 ,  F01D21/003 ,  F02C9/28 ,  F05D2220/323 ,  F05D2260/83 ,  F05D2270/07 ,  F05D2270/71

Abstract: A method of operating an aircraft that includes a propulsion system. The propulsion system includes a gas turbine engine and a fuel tank arranged to provide fuel to the gas turbine engine. The method includes: determining at least one fuel characteristic of the fuel arranged to be provided to the gas turbine engine; and controlling the propulsion system based on the at least one fuel characteristic.

公开(公告)号：US12060838B2

公开(公告)日：2024-08-13

申请号：US18099490

申请日：2023-01-20

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: G01N21/33 ,  B64D27/10 ,  B64D47/00 ,  F02C9/00 ,  G01N21/3577 ,  G01N21/64 ,  G01N33/28 ,  B64D37/00 ,  G01N21/35

CPC classification number: F02C9/00 ,  B64D27/10 ,  B64D47/00 ,  G01N21/33 ,  G01N21/3577 ,  G01N21/64 ,  G01N33/287 ,  B64D37/00 ,  G01N2021/3595

Abstract: A method of generating a maintenance schedule for an aircraft including one or more gas turbine engines powered by an aviation fuel. The method includes: determining one or more fuel characteristics of the fuel; and generating a maintenance schedule according to the one or more fuel characteristics. Also disclosed is a method of maintaining an aircraft, a maintenance schedule generation system and an aircraft.

公开(公告)号：US12044177B2

公开(公告)日：2024-07-23

申请号：US18337636

申请日：2023-06-20

Applicant: ROLLS-ROYCE plc

Inventor： Craig W Bemment ,  Alastair G Hobday ,  Benjamin J Keeler ,  Christopher P Madden ,  Andrea Minelli ,  Andrew T Smith ,  Peter Swann ,  Martin K Yates

IPC: F02C7/224 ,  F02C9/28 ,  F23R3/28

CPC classification number: F02C7/224 ,  F02C9/28 ,  F23R3/28 ,  F05D2260/221

Abstract: A method of operating a gas turbine engine is disclosed, the gas turbine engine comprising a combustor arranged to combust a fuel; and a fuel management system arranged to provide the fuel to the combustor. The fuel management system comprises two fuel-oil heat exchangers through which oil and the fuel flow, the heat exchangers arranged to transfer heat to the fuel and comprising a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger; and a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located between the two heat exchangers. The method comprises controlling the fuel management system so as to transfer between 200 and 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：US11643980B1

公开(公告)日：2023-05-09

申请号：US17853233

申请日：2022-06-29

Applicant: ROLLS-ROYCE plc

Inventor： Craig W Bemment ,  Benjamin J Keeler ,  Paul W Ferra ,  Alastair G Hobday ,  Kevin R McNally ,  Andrea Minelli ,  Martin K Yates

IPC: F02C9/28

CPC classification number: F02C9/28 ,  F05D2220/323 ,  F05D2270/30

Abstract: A method of determining a calorific value of fuel supplied to a gas turbine engine of an aircraft comprises sensing at least one engine parameter during a first time period of aircraft operation during which the gas turbine engine uses the fuel; and, based on the at least one sensed engine parameter, determining a calorific value of the fuel. The sensing may be repeated such that the at least one engine parameter is monitored over time. The gas turbine engine may be a propulsive gas turbine engine of the aircraft or a gas turbine engine of an auxiliary power unit of the aircraft.

公开(公告)号：US11585278B1

公开(公告)日：2023-02-21

申请号：US17853144

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: G01N21/35 ,  F02C9/00 ,  B64D27/10 ,  B64D47/00 ,  G01N33/28 ,  G01N21/64 ,  G01N21/33 ,  G01N21/3577 ,  B64D37/00

Abstract: A method of determining one or more fuel characteristics of an aviation fuel for powering a gas turbine engine of an aircraft includes: measuring one or more trace substance parameters of the fuel, the one or more trace substance parameters each associated with a respective trace substance in the fuel; and determining one or more fuel characteristics of the fuel based on the one or more trace substance parameters. Further, a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.

公开(公告)号：US11434832B2

公开(公告)日：2022-09-06

申请号：US17411617

申请日：2021-08-25

Applicant: ROLLS-ROYCE plc

Inventor： Craig W Bemment

IPC: F02C9/24 ,  F02C9/18 ,  F01D19/00 ,  F02C7/36 ,  F02C7/268

Abstract: A gas turbine engine for an aircraft and a method of operating a gas turbine engine on an aircraft. Embodiments disclosed include a gas turbine engine for an aircraft including: an engine core has a turbine, a compressor, and a core shaft; a fan located upstream of the engine core, the fan has a plurality of fan blades; a nacelle surrounding the engine core and defining a bypass duct and bypass exhaust nozzle; and a gearbox that receives an input from the core shaft and outputs drive to the fan wherein the gas turbine engine is configured such that a jet velocity ratio of a first jet velocity exiting from the bypass exhaust nozzle to a second jet velocity exiting from an exhaust nozzle of the engine core at idle conditions is greater by a factor of 2 or more than the jet velocity ratio at maximum take-off conditions.

公开(公告)号：US11326512B2

公开(公告)日：2022-05-10

申请号：US17345588

申请日：2021-06-11

Applicant: ROLLS-ROYCE PLC

Inventor： Craig W Bemment ,  Pascal Dunning

IPC: F02C7/36 ,  F02C3/04

Abstract: A gas turbine engine for an aircraft comprises an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, wherein a compressor exit temperature is defined as an average temperature of airflow at the exit from the compressor; and a fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, each fan blade having a leading edge and a trailing edge, wherein a fan rotor entry temperature is defined as an average temperature of airflow across the leading edge of each fan blade at cruise conditions and a fan tip rotor exit temperature is defined as an average temperature of airflow across a radially outer portion of each fan blade at the trailing edge at cruise conditions. A core to fan tip temperature rise ratio is in the range from 2.845 to 3.8.

公开(公告)号：US11181042B2

公开(公告)日：2021-11-23

申请号：US16411347

申请日：2019-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Michael O Hales ,  Craig W Bemment ,  Stephane M M Baralon ,  Benjamin J Sellers ,  Christopher Benson ,  Benedict R Phelps ,  Mark J Wilson

IPC: F02C3/073 ,  F02C7/36

Abstract: A gas turbine engine has a cycle operability parameter β in a defined range to achieve improved overall performance, taking into account fan operability and/or bird strike requirements as well as engine efficiency. The defined range of cycle operability parameter β may be particularly beneficial for gas turbine engines in which the fan is driven by a turbine through a gearbox.

公开(公告)号：US12297770B2

公开(公告)日：2025-05-13

申请号：US18405485

申请日：2024-01-05

Applicant: ROLLS-ROYCE plc

Inventor： Craig W Bemment ,  Pascal Dunning

IPC: F02C3/04 ,  F02C7/36 ,  F02K3/06

Abstract: A gas turbine engine for an aircraft comprises an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, wherein a compressor exit temperature is defined as an average temperature of airflow at the exit from the compressor; and a fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, each fan blade having a leading edge and a trailing edge, wherein a fan rotor entry temperature is defined as an average temperature of airflow across the leading edge of each fan blade at cruise conditions and a fan tip rotor exit temperature is defined as an average temperature of airflow across a radially outer portion of each fan blade at the trailing edge at cruise conditions. A core to fan tip temperature rise ratio is in the range from 2.845 to 3.8.

公开(公告)号：US12241423B2

公开(公告)日：2025-03-04

申请号：US18125431

申请日：2023-03-23

Applicant: ROLLS-ROYCE PLC

Inventor： Craig W Bemment ,  Benjamin J Keeler ,  Paul W Ferra ,  Alastair G Hobday ,  Kevin R McNally ,  Andrea Minelli ,  Martin K. Yates

IPC: F02C9/40 ,  F02C9/28

Abstract: A method of refuelling an aircraft comprising a gas turbine engine and a fuel tank arranged to provide fuel to the gas turbine engine comprises obtaining an amount of energy required for an intended flight profile; obtaining a calorific value of fuel available to the aircraft for refuelling; calculating the amount of the available fuel needed to provide the required energy; and refuelling the aircraft with the calculated amount of the available fuel. The calculating the amount of the available fuel needed to provide the required energy may comprise obtaining an energy content of fuel already in the fuel tank and subtracting that from the determined amount of energy required for the intended flight profile.