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公开(公告)号：US20240401531A1
公开(公告)日：2024-12-05
申请号：US18420204
申请日：2024-01-23
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 and a gas turbine engine includes 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. A fuel viscosity is adjusted to a maximum of 0.58 mm2/s on entry to the combustor at cruise conditions.
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公开(公告)号：US20240110517A1
公开(公告)日：2024-04-04
申请号：US18372836
申请日：2023-09-26
Applicant: ROLLS-ROYCE plc
Inventor： Andrea MINELLI
CPC classification number: F02C7/18 , F02C7/06 , F02C7/32 , F05D2260/232 , F05D2260/98
Abstract: A method of operating a gas turbine engine for an aircraft including: a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor; a fan; turbomachinery bearings; a power gearbox; and a heat management system configured to provide lubrication and cooling to the gearbox and turbomachinery bearings. The method includes operating the heat management system to provide a first amount of heat and a second amount of heat such that a first proportion of heat generated by the gearbox and the turbomachinery and dissipated to air at 85% of a core shaft maximum take-off speed is in the range of from 0.25 to 0.70; and operating the fan at cruise condition to provide a fan pressure ratio in the range of from 1.35 to 1.43.
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公开(公告)号：US20240110508A1
公开(公告)日：2024-04-04
申请号：US18372814
申请日：2023-09-26
Applicant: ROLLS-ROYCE plc
Inventor： Andrea MINELLI
Abstract: A geared gas turbine engine includes a heat management system configured to provide lubrication and cooling to a power gearbox and turbomachinery bearings, and including a pipe assembly adapted to provide a lubricant flow to the power gearbox and turbomachinery bearings to remove the heat generated by the power gearbox and turbomachinery bearings, an air-lubricant heat exchanger to dissipate a first amount of heat, and a fuel-lubricant heat exchanger to dissipate a second amount of heat wherein the heat management system is configured to provide the first amount of heat and the second amount of heat such that at cruise conditions a proportion of heat generated by the gearbox and the turbomachinery and dissipated to air is in the range of from 0.35 to 0.80.
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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：US20240210038A1
公开(公告)日：2024-06-27
申请号：US18211793
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: F23R3/346 , F02C7/224 , F23K5/08 , F23K2300/204
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 lower the fuel viscosity to 0.58 mm2/s or lower on entry to the combustor at cruise conditions.
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Patent Agency Ranking
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：US20240110510A1
公开(公告)日：2024-04-04
申请号：US18169619
申请日：2023-02-15
Applicant: ROLLS-ROYCE plc
Inventor： Andrea MINELLI
CPC classification number: F02C7/12 , F02C7/06 , F02C7/36 , F05D2240/50 , F05D2260/2214
Abstract: A gas turbine engine for an aircraft includes: an engine core; a fan; turbomachinery bearings; a power gearbox; and a heat management system for providing lubrication and cooling to the power gearbox and turbomachinery bearings, at least one air-lubricant heat exchanger to dissipate a first amount of heat to a first heat sink, and at least one fuel-lubricant heat exchanger to dissipate a second amount of heat to a second heat sink, wherein the heat management system is configured to provide a first amount of heat and a second amount of heat such that a ratio of a first proportion of heat generated by the gearbox and the turbomachinery and dissipated to air at 85% of a core shaft maximum take-off speed at an environment temperature of ISA +40° C. to the first proportion at an environment temperature of ISA −69° C. is in the range of from 1.5 to 4.5.
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公开(公告)号：US20230243305A1
公开(公告)日：2023-08-03
申请号：US18096146
申请日：2023-01-12
Applicant: ROLLS-ROYCE plc
Inventor： Andrea MINELLI
CPC classification number: F02C7/16 , F02C3/06 , F02C7/22 , F02C7/06 , F05D2220/323 , F05D2240/35 , F05D2260/213 , F05D2260/232 , F05D2260/98
Abstract: A combination of a gas turbine engine and power electronics, includes an engine core and oil circuit to cool and lubricate bearings of the engine core, and a fuel circuit for supplying fuel to the combustor. The fuel circuit includes a low pressure pump for pressurising the fuel to a low pressure, and a high pressure pump to receive the low pressure fuel and increase the pressure to a high pressure for supply to a fuel metering system and the combustor. The engine includes a fuel-oil heat exchanger having a fuel side on the fuel circuit between an outlet of the low pressure pump and an inlet of the high pressure pump, and an oil side on the oil circuit to transfer heat from the oil circuit to the fuel circuit. The power electronics transfers heat to a cooling flow formed by a portion of the low pressure fuel.
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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：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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