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公开(公告)号：US20230323824A1
公开(公告)日：2023-10-12
申请号：US18098433
申请日：2023-01-18
Applicant: ROLLS-ROYCE PLC
Inventor： Peter SWANN , Christopher P MADDEN , Craig W BEMMENT
CPC classification number: F02C9/40 , F02C9/28 , F05D2270/31 , F05D2220/323 , F05D2270/306 , F05D2220/80
Abstract: A aircraft gas turbine engine and operation method, the engine including: a staged combustion system having pilot and main fuel injectors, and operates in a pilot-only range wherein fuel delivers to pilot fuel injectors, and a pilot-and-main operation range wherein fuel is delivered to at least the main fuel injectors. The engine further includes a fuel delivery regulator to pilot and main fuel injectors, which receives fuel from a first and second source containing fuels each with different characteristics. The staged combustion system switches between pilot-only and pilot-and-main range operation when in steady cruise mode, the mode defining a boundary between first and second engine cruise operation range. The fuel delivery regulator delivers fuel to pilot fuel injectors during at least part of the first engine cruise operation with different fuel characteristics from fuel delivered to one or both pilot and main fuel injectors the second engine cruise operation range.
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公开(公告)号：US20240418129A1
公开(公告)日：2024-12-19
申请号：US18421471
申请日：2024-01-24
Applicant: ROLLS-ROYCE PLC
Inventor： Christopher P MADDEN , Craig W BEMMRNT , Andrew T SMITH , Peter SWANN
Abstract: There is provided a method of operating a gas turbine engine including a combustor. The combustor includes a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the chamber. The nozzles include a first and second subset of fuel spray nozzles. The combustor is operable in a condition wherein the first subset is supplied with more fuel than the second. A ratio of the number of nozzles in the first subset to the second is 1:2 to 1:5. The method includes operating the engine so a reduction of 20-80% in an average of particles/kg of nvPM in the exhaust when the engine is operating at 85% available thrust for given operating conditions and when the engine is operating at 30% is obtained when fuel provided to the nozzles is a sustainable aviation fuel instead of a fossil-based hydrocarbon fuel. Also provided is a gas turbine engine for an aircraft.
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公开(公告)号：US20240210037A1
公开(公告)日：2024-06-27
申请号：US18211624
申请日：2023-06-20
Applicant: ROLLS-ROYCE plc
Inventor： Christopher P MADDEN , Craig W BEMMENT , Andrew T SMITH , Peter SWANN
CPC classification number: F02C9/40 , F02C3/20 , F23R3/28 , F05D2240/35 , F05D2270/08
Abstract: A method of operating a gas turbine engine including a combustor. The combustor includes a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the chamber. The nozzles include a first and second subset of fuel spray nozzles. The combustor is operable in a condition wherein the first subset is supplied with more fuel than the second. A ratio of the number of nozzles in the first subset to the second is 1:2 to 1:5. The method includes operating the engine so a reduction of 20-80% in an average of particles/kg of nvPM in the exhaust when the engine is operating at 85% available thrust for given operating conditions and when the engine is operating at 30% is obtained when fuel provided to the nozzles is a sustainable aviation fuel instead of a fossil-based hydrocarbon fuel. Also, a gas turbine engine for an aircraft.
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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
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.
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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
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.
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Patent Agency Ranking
公开(公告)号：US20230323820A1
公开(公告)日：2023-10-12
申请号：US17853191
申请日：2022-06-29
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN , Craig W BEMMENT , Christopher P MADDEN
CPC classification number: F02C9/26 , F02C7/22 , B64D27/10 , B64D37/30 , F05D2220/323
Abstract: A gas turbine engine for an aircraft, including: staged combustion system having pilot fuel injectors and main fuel injectors, staged combustion system being operable in pilot-only range of operation and pilot-and-main range of operation; and fuel delivery regulator arranged to control delivery of fuel to pilot and main fuel injectors. Fuel delivery regulator arranged to receive fuel from a first fuel source containing a first fuel having a first fuel characteristic and a second fuel source containing a second fuel having a different second fuel characteristic. The fuel delivery regulator is arranged to deliver fuel to the pilot fuel injectors during at least part of the pilot-only range of operation having a different fuel characteristic from fuel delivered to one or both of the pilot and main fuel injectors during at least part of the pilot-and-main range of operation. A method of operating a gas turbine engine is also disclosed.
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公开(公告)号：US20240209787A1
公开(公告)日：2024-06-27
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
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.
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公开(公告)号：US20230323823A1
公开(公告)日：2023-10-12
申请号：US17853494
申请日：2022-06-29
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN , Christopher P MADDEN , Craig W BEMMENT
CPC classification number: F02C9/40 , F02C9/28 , F05D2220/323 , F05D2270/71 , F05D2270/306 , F05D2270/31 , F05D2270/08
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.
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公开(公告)号：US20230322395A1
公开(公告)日：2023-10-12
申请号：US18209136
申请日：2023-06-13
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN , Craig W BEMMENT , Alastair G HOBDAY , Benjamin J KEELER , Christopher P MADDEN
Abstract: A power system for an aircraft includes one or more gas turbine engines arranged to burn a fuel so as to provide power to the aircraft; a plurality of fuel tanks each arranged to contain a fuel to be used to provide power to the aircraft; and a fuel manager. At least two of the fuel tanks contain different fuels, which have different proportions of a sustainable aviation 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 select a specific fuel accordingly to power at least the majority of operations on the ground. The fuel manager may additionally identify which tank contains the fuel with the highest proportion of a sustainable aviation fuel; and that fuel may be used to power at least the majority of operations on the ground.
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公开(公告)号：US20230193836A1
公开(公告)日：2023-06-22
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: F02C9/28
CPC classification number: F02C9/28 , F05D2260/80 , F05D2270/303 , F05D2270/304 , F05D2270/708
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.
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