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公开(公告)号：US20230258101A1
公开(公告)日：2023-08-17
申请号：US18138333
申请日：2023-04-24
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
CPC classification number: F01D21/003 , F02C9/28 , F05D2270/0831 , F05D2270/804 , F05D2260/80 , F05D2220/323 , F05D2270/708
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 comprises: determining, during use of the gas turbine engine, one or more exhaust content parameters by performing a sensor measurement on an exhaust of the gas turbine engine; and determining one or more fuel characteristics of the fuel based on the one or more exhaust parameters including the nvPM content of the exhaust. 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：US20230192303A1
公开(公告)日：2023-06-22
申请号：US17853332
申请日：2022-06-29
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN , Craig W. BEMMENT , Alastair G. HOBDAY , Benjamin J. KEELER , Christopher P. MADDEN
Abstract: A propulsion system for an aircraft comprises a gas turbine engine; a plurality of fuel tanks arranged to contain different fuels to be used to power the gas turbine engine, wherein the fuels have different calorific values; and a fuel manager. The fuel manager is arranged to store information on the fuel contained in each fuel tank and to control fuel input to the gas turbine engine in operation by selection of a specific fuel or fuel combination from one or more of the plurality of fuel tanks based on thrust demand of the gas turbine engine such that a fuel with a lower calorific value is supplied to the gas turbine engine at lower thrust demand.
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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：US20240209801A1
公开(公告)日：2024-06-27
申请号：US18337545
申请日：2023-06-20
Applicant: ROLLS-ROYCE plc
Inventor： Christopher P. MADDEN , David M. BEAVEN , Craig W. BEMMENT , Paul W. FERRA , Benjamin J. KEELER , Peter SWANN , Martin K. YATES
CPC classification number: F02C9/40 , F02C3/20 , F23R3/28 , F05D2240/35
Abstract: There is provided a method of operating a gas turbine engine, the gas turbine engine comprising: a rich burn, quick quench, lean burn (RQL) combustor having a number of fuel spray nozzles in the range 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. The method comprises operating the gas turbine engine such that a reduction of 10-70% in an average of particles/kg of nvPM in the exhaust of the gas turbine engine when the engine 10 is operating at 85% available thrust for given operating conditions and particles/kg of nvPM in the exhaust of the gas turbine engine when the engine is operating at 30% available thrust for the given operating conditions is obtained when a fuel provided to the combustor is a sustainable aviation fuel instead of a fossil-based hydrocarbon fuel.
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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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Patent Agency Ranking
公开(公告)号：US20230313743A1
公开(公告)日：2023-10-05
申请号：US18328991
申请日：2023-06-05
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
IPC: F02C9/28
CPC classification number: F02C9/28 , F05D2260/80 , F05D2270/708 , F05D2270/304 , F05D2270/303 , F23N2221/10
Abstract: The present application provides 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 includes: passing UV-visual spectrum light through the fuel; measuring a transmittance parameter indicating the transmittance of light through the fuel; determining one or more fuel characteristics of the fuel based on the transmittance parameter; and communicating the one or more fuel characteristic to a control module of the gas turbine engine or the aircraft. 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：US20230193831A1
公开(公告)日：2023-06-22
申请号：US18096858
申请日：2023-01-13
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
CPC classification number: F02C9/00 , B64D27/10 , B64D47/00 , G01N33/287 , G01N21/64 , G01N21/33 , G01N21/3577 , G01N2021/3595
Abstract: A fuel characteristic determination system and method for determining one or more fuel characteristics of an aviation fuel for powering a gas turbine engine of an aircraft. The system includes a sensor component that is formed from a nitrile seal material and includes a surface that can be exposed to the fuel; a sensor for measuring a swell parameter of the seal material; and a fuel characteristics determination module for determining one or more fuel characteristics of the fuel based on the swell parameter. The method includes: exposing one or more seals of a fuel system of an aircraft to fuel within the fuel system; exposing a sensor component, made from the same material as the one or more seals, to the fuel; and measuring a swell parameter of the seal material.
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公开(公告)号：US20160265438A1
公开(公告)日：2016-09-15
申请号：US15044534
申请日：2016-02-16
Applicant: ROLLS-ROYCE plc
Inventor： Benjamin J. KEELER , Paul S. MCCABE
IPC: F02C7/14
CPC classification number: F02C7/14 , F02C7/224 , F05D2240/40 , Y02T50/675
Abstract: This invention concerns an engine fuel-oil heat exchange system for an engine (10) having a first fuel line (30) for delivery of fuel to an engine combustor (16) and a second fuel line (32) for delivery of fuel to ancillary engine equipment. The heat exchange system has a first heat exchanger (34) for transfer of heat from an engine oil system to the first fuel line (30) and a second heat exchanger (40) for transfer of heat from the engine oil system to the second fuel line (32). A control valve (46) is provided for selective control of the oil flow (48) from the engine oil system to the first (30) and second (32) heat exchangers.[FIG. 2]
Abstract translation: [图。 2]
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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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