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公开(公告)号：US20240318600A1
公开(公告)日：2024-09-26
申请号：US18677165
申请日：2024-05-29
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：US20240309817A1
公开(公告)日：2024-09-19
申请号：US18676832
申请日：2024-05-29
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 , F02C7/224 , 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：US20240301828A1
公开(公告)日：2024-09-12
申请号：US18663558
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
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.
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公开(公告)号：US20240209788A1
公开(公告)日：2024-06-27
申请号：US18337699
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
CPC classification number: F02C7/224 , F02C7/222 , F02C7/232 , F05D2270/07
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 raise the fuel temperature to an average of at least 135° C. on entry to the combustor at cruise conditions. Also provided is a gas turbine for an aircraft.
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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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Patent Agency Ranking
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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公开(公告)号：US20230193832A1
公开(公告)日：2023-06-22
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
CPC classification number: F02C9/00 , B64D47/00 , G01N21/3577 , B64D27/10 , G01N21/33 , G01N33/287 , G01N21/64 , B64D37/00
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.
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公开(公告)号：US20230193777A1
公开(公告)日：2023-06-22
申请号：US17853405
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
CPC classification number: F01D21/003 , F02C9/28 , F05D2220/323 , F05D2260/80 , F05D2270/0831 , F05D2270/708 , F05D2270/804
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 comprises: determining, during use of the gas turbine engine, one or more exhaust content parameters by performing a sensor measurement on an exhaust of the gas turbine engine; and determining one or more fuel characteristics of the fuel based on the one or more exhaust parameters. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.
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