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公开(公告)号：US20240263582A1
公开(公告)日：2024-08-08
申请号：US18634305
申请日：2024-04-12
申请人： Rolls-Royce plc
发明人： Craig W. BEMMENT , Alastair G. Hobday , Benjamin J. Keeler , Christopher P. Madden , Andrea Minelli , Andrew T. Smith , Peter Swann , Martin K. Yates
CPC分类号： F02C7/14 , F02C7/224 , F02C7/36 , F05D2220/323 , F05D2260/213
摘要： 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：US11821373B2
公开(公告)日：2023-11-21
申请号：US18053124
申请日：2022-11-07
申请人： ROLLS-ROYCE plc
发明人： Christopher P. Madden , Peter Swann
CPC分类号： F02C9/28 , F02C3/30 , F23R3/346 , F02C9/263 , F02C9/40 , F05D2270/08 , F05D2270/804
摘要： A gas turbine engine for an aircraft. The gas turbine comprises a staged combustion system having pilot injectors and main injectors, a fuel metering system configured to control fuel flow to the pilot injectors and the main injectors, and a fuel system controller. The controller is configured to identify an atmospheric condition, determine a ratio of pilot fuel flow rate for the pilot injectors to main fuel flow rate for the main injectors in response to the atmospheric condition, and inject fuel by the pilot injectors and the main injectors in accordance with said ratio to control an index of soot emissions caused by combustion of fuel therein.
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公开(公告)号：US11530651B2
公开(公告)日：2022-12-20
申请号：US17189650
申请日：2021-03-02
申请人： ROLLS-ROYCE plc
发明人： Christopher P. Madden , Peter Swann
摘要： A gas turbine engine for an aircraft. The gas turbine comprises a staged combustion system having pilot injectors and main injectors, a fuel metering system configured to control fuel flow to the pilot injectors and the main injectors, and a fuel system controller. The controller is configured to identify an atmospheric condition, determine a ratio of pilot fuel flow rate for the pilot injectors to main fuel flow rate for the main injectors in response to the atmospheric condition, and inject fuel by the pilot injectors and the main injectors in accordance with said ratio to control an index of soot emissions caused by combustion of fuel therein.
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公开(公告)号：US20240301829A1
公开(公告)日：2024-09-12
申请号：US18663599
申请日：2024-05-14
申请人： ROLLS-ROYCE plc
发明人： Craig W BEMMENT , Benjamin J. Keeler , Christopher P. Madden , Andrea Minelli , Peter Swann , Martin K. Yates
CPC分类号： F02C7/14 , F02C7/06 , F02C7/10 , F02C7/224 , F02C7/36 , F05D2220/323 , F05D2260/205 , F05D2260/213 , F05D2260/98
摘要： 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：US11530652B2
公开(公告)日：2022-12-20
申请号：US17189663
申请日：2021-03-02
申请人： ROLLS-ROYCE plc
发明人： Christopher P. Madden , Peter Swann
摘要： A gas turbine engine for an aircraft. The gas turbine comprises a combustor, a fuel injection system connected with a source of fuel and configured to inject fuel into the combustor, a water injection system connected with a source of water and which is configured to inject water into the combustor, and a control system. The control system is configured to identify an atmospheric condition; determine a water-fuel ratio for injection into the combustor of the gas turbine engine in response to the atmospheric condition; and control injection of fuel and water by the fuel injection system and the water injection system according to said water-fuel ratio to control an soot emissions caused by combustion of fuel therein.
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