公开(公告)号：US20240401531A1

公开(公告)日：2024-12-05

申请号：US18420204

申请日：2024-01-23

Applicant: ROLLS-ROYCE plc

Inventor： Craig W BEMMENT ,  Benjamin J KEELER ,  Kevin R MCNALLY ,  Andrea MINELLI

IPC: F02C7/14 ,  F02C7/16 ,  F02C7/22

Abstract: A method of operating a gas turbine engine and a gas turbine engine includes a fuel delivery system arranged to provide fuel, a combustor arranged to combust at least a proportion of the fuel, a primary fuel-oil heat exchanger arranged to have up to 100% of the fuel provided by the fuel delivery system flow therethrough, and a secondary fuel-oil heat exchanger arranged to have a proportion of the fuel from the primary fuel-oil heat exchanger flow therethrough. Fuel is arranged to flow from the primary fuel-oil heat exchanger to the secondary fuel-oil heat exchanger whereas oil is arranged to flow from the secondary fuel-oil heat exchanger to the primary fuel-oil heat exchanger. A fuel viscosity is adjusted to a maximum of 0.58 mm2/s on entry to the combustor at cruise conditions.

公开(公告)号：US20240210039A1

公开(公告)日：2024-06-27

申请号：US18337477

申请日：2023-06-20

Applicant: ROLLS-ROYCE PLC

Inventor： Christopher P MADDEN ,  David M BEAVEN ,  Craig W BEMMENT ,  Paul W FERRA ,  Barani P GUNASEKARAN ,  Benjamin J KEELER ,  Peter SWANN ,  Martin K YATES

IPC: F23R3/34 ,  F02C7/22 ,  F23K5/08

CPC classification number: F23R3/346 ,  F02C7/22 ,  F23K5/08 ,  F05D2240/35 ,  F23K2300/204

Abstract: There is provided a method of operating a gas turbine engine. The gas turbine engine comprises a staged combustor having an arrangement of fuel spray nozzles in which fuel flow is biased to a subset of the nozzles adjacent one or more ignitors during a re-light procedure. The method comprises transferring heat from the oil to the fuel before the fuel enters the combustor so as to lower the fuel viscosity to 0.58 mm2/s or lower on entry to the combustor at cruise conditions. Also disclosed is a gas turbine engine.

公开(公告)号：US20240210038A1

公开(公告)日：2024-06-27

申请号：US18211793

申请日：2023-06-20

Applicant: ROLLS-ROYCE PLC

Inventor： Christopher P MADDEN ,  Craig W BEMMENT ,  Paul W FERRA ,  Benjamin J KEELER ,  Andrea MINELLI ,  Peter SWANN ,  Martin K YATES

IPC: F23R3/34 ,  F02C7/224 ,  F23K5/08

CPC classification number: F23R3/346 ,  F02C7/224 ,  F23K5/08 ,  F23K2300/204

Abstract: A method of operating a gas turbine engine having a lean burn staged combustion system having a combustor in which fuel is combusted. The gas turbine engine includes a fuel-oil heat exchanger arranged to transfer heat between oil and fuel that is provided to the combustor. The method includes transferring heat from the oil to the fuel before the fuel enters the combustor so as to lower the fuel viscosity to 0.58 mm2/s or lower on entry to the combustor at cruise conditions.

公开(公告)号：US20230296060A1

公开(公告)日：2023-09-21

申请号：US18324619

申请日：2023-05-26

Applicant: ROLLS-ROYCE plc

Inventor： Peter SWANN ,  Craig W BEMMENT ,  Alastair G HOBDAY ,  Benjamin J KEELER ,  Christopher P MADDEN

IPC: F02C9/28 ,  B64D37/04 ,  G08G5/00 ,  B64D27/10

CPC classification number: F02C9/28 ,  B64D37/04 ,  G08G5/0034 ,  B64D27/10

Abstract: A method of operating an aircraft including a gas turbine engine and a plurality of fuel tanks arranged to provide fuel to the gas turbine engine. At least two of the fuel tanks contain fuels with different fuel characteristics. The method includes obtaining a flight profile for a portion of a flight of the aircraft; and determining a fueling schedule for the portion of the flight based on the flight profile and the fuel characteristics, the fueling schedule governing the variation with time of how much fuel is drawn from each tank. Fuel input to the gas turbine engine may then be controlled in operation in accordance with the fueling schedule.

公开(公告)号：US20240209789A1

公开(公告)日：2024-06-27

申请号：US18337717

申请日：2023-06-20

Applicant: ROLLS-ROYCE plc

Inventor： Craig W BEMMENT ,  Benjamin J KEELER ,  Kevin R MCNALLY ,  Andrea MINELLI

IPC: F02C7/224 ,  F02C7/06 ,  F02C7/32

CPC classification number: F02C7/224 ,  F02C7/06 ,  F02C7/32 ,  F05D2260/221 ,  F05D2260/98

Abstract: A method of operating a gas turbine engine having an engine core having a turbine, a compressor, a combustor to combust a fuel, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core; a fan shaft; a main gearbox receiving an input from the core shaft and outputting drive to the fan via the fan shaft; a primary oil loop system to supply oil to lubricate the main gearbox; and a heat exchange system arranged to transfer heat between the oil and the fuel, the oil having an average temperature of at least 180° C. on entry to the heat exchange system at cruise conditions. The method includes transferring 200 to 600 KJ/m3 of heat from the oil to the fuel, using the heat exchange system, at cruise conditions, which may facilitate control of the oil temperature on entry to the main gearbox.

公开(公告)号：US20240209786A1

公开(公告)日：2024-06-27

申请号：US18337603

申请日：2023-06-20

Applicant: ROLLS-ROYCE PLC

Inventor： Craig W BEMMENT ,  Benjamin J KEELER ,  Kevin R MCNALLY ,  Andrea MINELLI

IPC: F02C7/224 ,  F23R3/28

CPC classification number: F02C7/224 ,  F23R3/28 ,  F05D2260/20

Abstract: A method of operating a gas turbine engine is disclosed, the gas turbine engine comprising a fuel delivery system arranged to provide fuel; a combustor arranged to combust at least a proportion of the fuel; a primary fuel-oil heat exchanger arranged to have up to 100% of the fuel provided by the fuel delivery system flow therethrough; and a secondary fuel-oil heat exchanger arranged to have a proportion of the fuel from the primary fuel-oil heat exchanger flow therethrough. Fuel is arranged to flow from the primary fuel-oil heat exchanger to the secondary fuel-oil heat exchanger and oil is arranged to flow from the secondary fuel-oil heat exchanger to the primary fuel-oil heat exchanger. The method comprises 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：US20240117771A1

公开(公告)日：2024-04-11

申请号：US18212290

申请日：2023-06-21

Applicant: ROLLS-ROYCE PLC

Inventor： Benjamin J KEELER ,  David M BEAVEN ,  Craig W BEMMENT ,  Paul W FERRA ,  Kevin R MCNALLY ,  Andrea MINELLI ,  Martin K YATES

IPC: F02C9/28

CPC classification number: F02C9/28 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2270/3013 ,  F05D2270/303 ,  F05D2270/309

Abstract: A method of determining at least one fuel characteristic of a fuel provided to a gas turbine engine of an aircraft includes making an operational change, the operational change being effected by a controllable component of a propulsion system of which the gas turbine engine forms a part, and being arranged to affect operation of the gas turbine engine, sensing a response to the operational change; and determining the at least one fuel characteristic based on the response to the operational change.

公开(公告)号：US20240077036A1

公开(公告)日：2024-03-07

申请号：US18203993

申请日：2023-05-31

Applicant: ROLLS-ROYCE plc

Inventor： Peter SWANN ,  Craig W BEMMENT ,  Alastair G HOBDAY ,  Benjamin J KEELER ,  Christopher P MADDEN

IPC: F02C9/28 ,  B64D27/10 ,  B64D37/04 ,  G08G5/00

CPC classification number: F02C9/28 ,  B64D27/10 ,  B64D37/04 ,  G08G5/0034

Abstract: A method of operating an aircraft including 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 proposing or initiating a change to a flight profile of the aircraft based on the at least one fuel characteristic. For example, intended route and/or altitude of the aircraft may be changed based on the one or more fuel characteristics.

公开(公告)号：US20230332543A1

公开(公告)日：2023-10-19

申请号：US18337516

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: F02C7/14 ,  F02C7/224 ,  F02C7/36

CPC classification number: F02C7/14 ,  F02C7/224 ,  F02C7/36 ,  F05D2220/323 ,  F05D2260/213

Abstract: A method of operating a gas turbine engine including an engine core including a turbine, compressor, combustor to combust a fuel, and core shaft connecting the turbine and compressor; a fan upstream of the engine core; a fan shaft; a gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft; a primary oil loop system to supply oil to the gearbox; and a heat exchange system. The method includes controlling the heat exchange system to adjust fuel viscosity to be lower than or equal to 0.58 mm2/s on entry to the combustor at cruise conditions.

公开(公告)号：US20230323822A1

公开(公告)日：2023-10-12

申请号：US18125477

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: F02C9/28

CPC classification number: F02C9/28 ,  F05D2240/35 ,  B64D41/00

Abstract: The present application discloses a method of determining one or more fuel characteristics of an aviation fuel suitable for powering a gas turbine engine of an aircraft, the gas turbine engine having a combustor supplied with fuel from a fuel system, the method comprising: determining a mass of the fuel being supplied to the combustor; determining a corresponding volume of the fuel being supplied to the combustor; and determining one or more fuel characteristics based on the determined mass and volume. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.