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公开(公告)号：US12168957B2
公开(公告)日：2024-12-17
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
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.
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公开(公告)号：US12098679B2
公开(公告)日：2024-09-24
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
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：US12098675B2
公开(公告)日：2024-09-24
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：US11988144B2
公开(公告)日：2024-05-21
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：US11920514B1
公开(公告)日：2024-03-05
申请号：US18337749
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 , F02C7/16 , F02C7/22 , F05D2260/213 , F05D2260/98
Abstract: A gas turbine engine including 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. The method includes using at least one of the primary fuel-oil heat exchanger and the secondary fuel-oil heat exchanger to heat the fuel so as to adjust the fuel viscosity to a maximum of 0.58 mm2/s on entry to the combustor at cruise conditions.
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Patent Agency Ranking
公开(公告)号：US11859565B2
公开(公告)日：2024-01-02
申请号：US17853333
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: F02C9/28
CPC classification number: F02C9/28 , F05D2220/323 , F05D2240/35 , F05D2270/303 , F05D2270/309 , F05D2270/3013
Abstract: A gas turbine engine includes: a combustor that combust the fuel and having an exit, a combustor exit temperature (T40) is the average temperature of flow and a combustor exit pressure (P40) is the total pressure there; a turbine including a rotor having a leading edge and a trailing edge, and wherein a turbine rotor entry temperature (T41) is an average temperature of flow at the leading edge and a turbine rotor entry pressure (P41) is the total pressure there; and a compressor having an exit, wherein a compressor exit temperature (T30) is the average temperature of flow at the exit from the compressor and a compressor exit pressure (P30) is the total pressure there (all at cruise conditions). A method of determining at least one fuel characteristic includes changing a fuel supplied to the engine; and determining a change in a relationship between T30 or P30, T40 and T41, or of P40 and P41, respectively.
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公开(公告)号：US12297781B2
公开(公告)日：2025-05-13
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
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.
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公开(公告)号：US12196133B1
公开(公告)日：2025-01-14
申请号：US18753092
申请日：2024-06-25
Applicant: ROLLS-ROYCE plc
Inventor： Andrea Minelli , Craig W Bemment , Benjamin J Keeler , Kevin R McNally , Martin K Yates
Abstract: A method of operating an aircraft gas turbine engine including: a core including a turbine, a compressor, a combustor to combust fuel, and a core shaft connecting the turbine to the compressor; a fan upstream of the core; a fan shaft; a bearing supporting the fan shaft; an oil loop system supplying oil to the bearing; and a heat exchange system including: an air-oil heat exchanger through which oil in the oil loop system flows; and a fuel-oil heat exchanger through which oil in the oil loop system and fuel flow to transfer heat between the oil and the fuel; and a bypass pipe to allow a proportion of the oil to flow past one of the air-oil and the fuel-oil heat exchanger; and a bypass valve to allow the proportion of the oil sent through the bypass pipe to be varied.
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公开(公告)号：US12152497B2
公开(公告)日：2024-11-26
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
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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公开(公告)号：US12098677B2
公开(公告)日：2024-09-24
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 , 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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