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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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公开(公告)号：US20240110513A1
公开(公告)日：2024-04-04
申请号：US18169658
申请日：2023-02-15
Applicant: ROLLS-ROYCE plc
Inventor： Andrea MINELLI
CPC classification number: F02C7/16 , F01D25/125 , F05D2220/323 , F05D2260/213 , F05D2260/232
Abstract: A gas turbine engine for an aircraft includes: an engine core including a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor; a fan including a plurality of fan blades and arranged upstream of the engine core; turbomachinery bearings; a power gearbox adapted to drive the fan at a lower rotation speed than the turbine; and a heat management system configured to provide lubrication and cooling to the power gearbox and turbomachinery bearings.
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公开(公告)号：US20240110511A1
公开(公告)日：2024-04-04
申请号：US18169611
申请日：2023-02-15
Applicant: ROLLS-ROYCE plc
Inventor： Andrea MINELLI
CPC classification number: F02C7/14 , F02C7/06 , F02C7/36 , F05D2220/323 , F05D2220/36 , F05D2260/213 , F05D2260/98
Abstract: A gas turbine engine for an aircraft includes: an engine core including a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor, wherein the core shaft has a core shaft maximum take-off speed in the range of 5500 rpm to 9500 rpm, preferably in the range of 5500 rpm to 8500 rpm; a fan; turbomachinery bearings; a power gearbox adapted to drive the fan at a lower rotation speed than the turbine; and a heat management system configured to provide lubrication and cooling to the gearbox and turbomachinery bearings, and including a pipe assembly adapted to provide a lubricant flow to the 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.
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公开(公告)号：US20240084734A1
公开(公告)日：2024-03-14
申请号：US18169667
申请日：2023-02-15
Applicant: ROLLS-ROYCE plc
Inventor： Andrea MINELLI
CPC classification number: F02C7/14 , F02C7/224 , F05D2220/323 , F05D2260/213
Abstract: A gas turbine engine for an aircraft includes: an engine core; fan; turbomachinery bearings; power gearbox; and a heat management system configured to provide lubrication and cooling to the power gearbox and turbomachinery bearings and including 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 proportion of heat generated by the power gearbox and the turbomachinery and dissipated to air at 85% of a core shaft maximum take-off speed in the range of 0.25 to 0.70, and a second proportion of heat generated by the power gearbox and the turbomachinery and dissipated to air at 65% of the core shaft maximum take-off speed in the range of 0.60 to 1.
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公开(公告)号：US20240271566A1
公开(公告)日：2024-08-15
申请号：US18643441
申请日：2024-04-23
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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Patent Agency Ranking
公开(公告)号：US20240209789A1
公开(公告)日：2024-06-27
申请号：US18337717
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: F02C7/224 , F02C7/06 , F02C7/32 , F05D2260/221 , F05D2260/98
Abstract: A method of operating a gas turbine engine having an engine core having a turbine, a compressor, a combustor 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 main gearbox receiving an input from the core shaft and outputting 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 arranged 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 200 to 600 KJ/m3 of heat from the oil to the fuel, using the heat exchange system, at cruise conditions, which may facilitate control of the oil temperature on entry to the main gearbox.
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公开(公告)号：US20240209786A1
公开(公告)日：2024-06-27
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
CPC classification number: F02C7/224 , F23R3/28 , F05D2260/20
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：US20240209779A1
公开(公告)日：2024-06-27
申请号：US18337519
申请日：2023-06-20
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 method of operating a gas turbine engine including an engine core and 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 main gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft, the main gearbox including gears and journal bearings; a recirculating lubrication system arranged to supply oil to lubricate the gears and journal bearings, the lubrication system including a first oil tank arranged to supply oil to the gears and journal bearings and a second oil tank arranged to supply oil to the journal bearings only. The method includes, at cruise conditions: transferring 200-600 KJ/m3 of heat to the fuel from the oil through the heat exchange system so as to control the oil temperature.
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公开(公告)号：US20240117771A1
公开(公告)日：2024-04-11
申请号：US18212290
申请日：2023-06-21
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 , F05D2270/3013 , F05D2270/303 , F05D2270/309
Abstract: A method of determining at least one fuel characteristic of a fuel provided to a gas turbine engine of an aircraft includes making an operational change, the operational change being effected by a controllable component of a propulsion system of which the gas turbine engine forms a part, and being arranged to affect operation of the gas turbine engine, sensing a response to the operational change; and determining the at least one fuel characteristic based on the response to the operational change.
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公开(公告)号：US20240110514A1
公开(公告)日：2024-04-04
申请号：US18372825
申请日：2023-09-26
Applicant: ROLLS-ROYCE plc
Inventor： Andrea MINELLI
CPC classification number: F02C7/16 , F02C3/06 , F02C7/36 , F05D2260/213 , F05D2260/4031
Abstract: An aircraft gas turbine engine includes: an engine core including a compressor, combustor, turbine, and a core shaft connecting the turbine to the compressor; a fan including fan blades and arranged upstream of the engine core; turbomachinery bearings; a power gearbox to drive the fan at a lower rotation speed than the turbine; and a heat management system providing lubrication and cooling to the 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, 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 first heat sink is air and the second heat sink is fuel.
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