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公开(公告)号：US20230193838A1
公开(公告)日：2023-06-22
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
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.
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公开(公告)号：US20240352898A1
公开(公告)日：2024-10-24
申请号：US18755944
申请日：2024-06-27
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN , Craig W. BEMMENT , Alastair G. HOBDAY , Benjamin J. KEELER , Christopher P. MADDEN
CPC classification number: F02C9/40 , F01D21/003 , F02C9/28 , F05D2220/323 , F05D2260/83 , F05D2270/07 , F05D2270/71
Abstract: A power system for an aircraft comprises a gas turbine engine, arranged to burn a fuel in a combustor so as to provide power to the aircraft; a plurality of fuel tanks arranged to contain fuel to be used to provide power to the aircraft; and a fuel manager. A first fuel tank of the plurality of fuel tanks is arranged to contain a first fuel, and a second tank of the plurality of fuel tanks is arranged to contain a second, different, fuel. The fuel manager is arranged to store information on the fuel contained in each fuel tank and to control fuel supply so as to take fuel from the second tank for engine start-up, before switching to the first fuel tank.
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公开(公告)号：US20240209799A1
公开(公告)日：2024-06-27
申请号：US18337568
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
CPC classification number: F02C9/38 , F02C7/14 , F02C7/16 , F05D2260/213
Abstract: A method of operating a gas turbine engine including: a combustor arranged to combust a fuel; and a fuel management system arranged to provide the fuel to the combustor, wherein the fuel management system includes two fuel-oil heat exchangers through which oil and fuel flow, which are arranged to transfer heat between the oil and fuel and include primary and secondary fuel-oil heat exchangers; a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located between the heat exchangers; and a recirculation valve located downstream of the primary heat exchanger, the recirculation valve arranged to allow a controlled amount of fuel which has passed through the primary heat exchanger to be returned to the inlet. The method includes selecting one or more fuels such that the calorific value of the fuel provided to the gas turbine engine is at least 43.5 MJ/kg.
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公开(公告)号：US20240209791A1
公开(公告)日：2024-06-27
申请号：US18337615
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
CPC classification number: F23R3/28 , F02C7/222 , F02C7/264 , F05D2240/35
Abstract: There is provided a method of operating a gas turbine engine. The gas turbine engine comprises a staged combustor comprising 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 providing fuel to the combustor having a calorific value of at least 43.5 MJ/kg. Also disclosed is a gas turbine engine.
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公开(公告)号：US20240209784A1
公开(公告)日：2024-06-27
申请号：US18337491
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
CPC classification number: F02C7/14 , F02C3/06 , F02C6/20 , F02C7/18 , F05D2220/323 , F05D2260/213 , F05D2260/232
Abstract: A method of operating a gas turbine engine including an engine core including: a turbine, compressor, combustor, core shaft; fan; fan shaft; gearbox that receives input from the core shaft and outputs drive to the fan via the fan shaft; primary oil loop system that supplies oil to the gearbox; and heat exchange system, which includes an air-oil heat exchanger through which oil in the primary oil loop system flows; and a fuel-oil heat exchanger through which the oil and fuel flow so heat is transferred therebetween, wherein the system branches so oil flows along each branch and the exchangers are arranged in parallel on different branches of the system; and a modulation valve that allows the oil sent via each branch to be varied. The method includes controlling the heat exchange system to raise the fuel temperature to at least 135° C. on entry to the combustor at cruise conditions.
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Patent Agency Ranking
公开(公告)号：US20230193835A1
公开(公告)日：2023-06-22
申请号：US17853074
申请日：2022-06-29
Applicant: ROLLS-ROYCE PLC
Inventor： Peter SWANN , Craig W. BEMMENT , Alastair G. HOBDAY , Benjamin J. KEELER , Christopher P. MADDEN
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 plurality of fuel tanks arranged to provide fuel to the gas turbine engine, where at least two of the fuel tanks contain fuels with different fuel characteristics. The method includes obtaining a flight profile for a flight of the aircraft; and determining a fuelling schedule for the flight based on the flight profile and the fuel characteristics. The fuelling schedule governs 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 fuelling schedule.
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公开(公告)号：US20250059923A1
公开(公告)日：2025-02-20
申请号：US18933409
申请日：2024-10-31
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
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 method comprising: determining a mass of a fuel being loaded, or which has been loaded, onto the aircraft; determining a corresponding volume of the fuel; determining one or more fuel characteristics of the fuel based on the determined mass and volume. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.
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公开(公告)号：US20240209800A1
公开(公告)日：2024-06-27
申请号：US18337531
申请日：2023-06-20
Applicant: ROLLS-ROYCE plc
Inventor： Christopher P. MADDEN , David M. BEAVEN , Craig W. BEMMENT , Paul W. FERRA , Benjamin J. KEELER , Peter SWANN
Abstract: Provided is a method of operating a gas turbine engine. The engine includes a combustor having a plurality of fuel spray nozzles and a fuel system arranged to provide fuel to the combustor. The system includes: fuel pump; fuel distributing valve downstream of the pump arranged to distribute fuel to the plurality of nozzles and bias fuel flow to the nozzles such that a first subset of the plurality of nozzles receives more fuel than a second subset of the plurality of nozzles; and fuel-oil heat exchanger. The method includes providing a fuel to the combustor and transferring heat from oil to the fuel in the fuel-oil heat exchanger before the fuel enters the combustor so as to lower a viscosity of the fuel to 0.58 mm2/s or lower on entry to the combustor at cruise conditions. Also provided is a gas turbine engine for an aircraft.
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公开(公告)号：US20240209780A1
公开(公告)日：2024-06-27
申请号：US18337546
申请日：2023-06-20
Applicant: ROLLS-ROYCE PLC
Inventor： Craig W. BEMMENT , Benjamin J. KEELER , Kevin R. MCNALLY , Andrea MINELLI
CPC classification number: F02C7/14 , F02C7/36 , F23K5/20 , F05D2260/20 , F23K2300/204
Abstract: A method of operating a gas turbine engine, the engine including an engine core with a turbine, a compressor, a combustor arranged to combust a fuel, and a core shaft connecting the turbine to the compressor; a fan upstream of the engine core; a fan shaft; a main 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 lubricate the main gearbox; and a heat exchange system 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 heat from the oil to the fuel to lower the fuel viscosity to a value of less than or equal to 0.58 mm2/s on entry to the combustor at cruise conditions.
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公开(公告)号：US20230313701A1
公开(公告)日：2023-10-05
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
CPC classification number: F01D21/003 , F02C9/28 , F05D2220/323 , F05D2270/804 , F05D2270/0831 , F05D2270/708 , F05D2260/80
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.
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