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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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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.
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公开(公告)号：US20230193834A1
公开(公告)日：2023-06-22
申请号：US17853117
申请日：2022-06-29
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: F02C9/22
CPC classification number: F02C9/22 , F05D2270/07 , F05D2270/309 , F05D2220/323
Abstract: A method of controlling a propulsion system of an aircraft, the propulsion system comprising a gas turbine engine arranged to be powered by a fuel and at least one variable inlet guide vane—VIGV, comprises obtaining at least one fuel characteristic of the fuel being provided to the gas turbine engine; and making a change to scheduling of the at least one VIGV based on the at least one obtained fuel characteristic.
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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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Patent Agency Ranking
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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公开(公告)号：US20240209785A1
公开(公告)日：2024-06-27
申请号：US18337497
申请日：2023-06-20
Applicant: ROLLS-ROYCE plc
Inventor： Craig W. BEMMENT , Alastair G. HOBDAY , Benjamin J. KEELER , Andrea MINELLI , Andrew T. SMITH , Martin K. YATES
CPC classification number: F02C7/224 , F02C7/14 , F02C7/32 , F23R3/005 , F05D2260/20
Abstract: A method of operating a gas turbine engine having an engine core having a turbine, a compressor, a combustor arranged 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 gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft; a heat exchange system having at least one fuel-oil heat exchanger arranged to transfer heat to the fuel; and a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located downstream of the at least one fuel-oil heat exchanger. The method includes operating the gas turbine engine using a fuel having a lubricity of between 0.71 mm and 0.90 mm wear scar diameter (WSD) at 25° C.
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公开(公告)号：US20230324319A1
公开(公告)日：2023-10-12
申请号：US17853184
申请日：2022-06-29
Applicant: ROLLS-ROYCE PLC
Inventor： Craig W. BEMMENT , Paul W. FERRA , Alastair G. HOBDAY , Benjamin J. KEELER , Kevin R. MCNALLY , Andrea MINELLI , Martin K. YATES
CPC classification number: G01N25/22 , F02C7/22 , F05D2220/323
Abstract: A method of checking refuelling of an aircraft comprising a gas turbine engine and a fuel tank arranged to provide fuel to the gas turbine engine comprises: receiving an input of calorific value data for fuel provided to the aircraft on refuelling; independently determining at least one of: (i) the calorific value of fuel supplied to the gas turbine engine in use; and (ii) the calorific value of the fuel provided to the aircraft on refuelling; and providing an alert if the determined calorific value is inconsistent with the calorific value data input received
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