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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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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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Patent Agency Ranking
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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公开(公告)号：US20230392555A1
公开(公告)日：2023-12-07
申请号：US18325240
申请日：2023-05-30
Applicant: Rolls-Royce Deutschland Ltd & Co KG , Rolls-Royce plc
Inventor： Ivo MARTIN , Björn PETERSEN , Andrea MINELLI
CPC classification number: F02C7/36 , F02C7/06 , F05D2260/98 , F05D2260/40311 , B64D35/02
Abstract: The invention relates to a planetary gearbox device with a static ring gear, a rotatable planet carrier, a plurality of planet gears, each planet gear being connected to a bearing device, wherein at least one of the bearing devices is coupled to at least one lubricant scooping device and/or at least one lubricant reservoir device for collecting lubricant, in particular oil coming from the at least one bearing device, and at least one lubricant channel is for allowing a flow of the collected lubricant towards a lubrication location and/or a lubricant supply for the planetary gearbox device.
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