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公开(公告)号：US20210108570A1
公开(公告)日：2021-04-15
申请号：US16992211
申请日：2020-08-13
Applicant: ROLLS-ROYCE PLC
Inventor： Craig W. BEMMENT
Abstract: There is provided a gas turbine engine comprising a low pressure shaft and a high pressure shaft; wherein the low pressure shaft connects a fan to a fan drive turbine, and the high pressure shaft connects a high pressure turbine to a compressor section. The low pressure shaft and the high pressure shaft are arranged such that when operating at idle the idle shaft speed ratio is greater than 6.05. The idle shaft speed ratio is the ratio of the speed of the high pressure shaft to the speed of the low pressure shaft at idle conditions.
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公开(公告)号：US20200370481A1
公开(公告)日：2020-11-26
申请号：US16526221
申请日：2019-07-30
Applicant: ROLLS-ROYCE plc
Inventor： Craig W. BEMMENT
Abstract: A gas turbine engine for an aircraft and a method of operating a gas turbine engine on an aircraft. Embodiments disclosed include a gas turbine engine for an aircraft including: an engine core has a turbine, a compressor, and a core shaft; a fan located upstream of the engine core, the fan has a plurality of fan blades; a nacelle surrounding the engine core and defining a bypass duct and bypass exhaust nozzle; and a gearbox that receives an input from the core shaft and outputs drive to the fan wherein the gas turbine engine is configured such that a jet velocity ratio of a first jet velocity exiting from the bypass exhaust nozzle to a second jet velocity exiting from an exhaust nozzle of the engine core at idle conditions is greater by a factor of 2 or more than the jet velocity ratio at maximum take-off conditions.
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公开(公告)号：US20200025073A1
公开(公告)日：2020-01-23
申请号：US16396918
申请日：2019-04-29
Applicant: ROLLS-ROYCE plc
Inventor： Craig W. BEMMENT , David P. SCOTHERN
Abstract: A method of operating a gas turbine engine compressor. The engine comprises a compressor having an environmental control system bleed port having an outlet in fluid communication with an aircraft environmental control system air duct, and an air turbine starter configured to rotate a compressor shaft of the gas turbine engine. The air turbine starter has an inlet in fluid communication with the environmental control system air duct via an air turbine valve. The method comprises determining a surge margin of the compressor, and where the surge margin of the compressor is determined to be below a predetermined minimum surge margin, opening the air turbine valve to supply air to the air turbine.
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公开(公告)号：US20240376845A1
公开(公告)日：2024-11-14
申请号：US18777670
申请日：2024-07-19
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, the gas turbine engine including an engine core comprising a 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; a primary oil loop system arranged 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 controlling the heat exchange system so as 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：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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Patent Agency Ranking
公开(公告)号：US20240309817A1
公开(公告)日：2024-09-19
申请号：US18676832
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: F02C9/38 , F02C7/14 , F02C7/16 , F02C7/224 , 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：US20240287937A1
公开(公告)日：2024-08-29
申请号：US18657237
申请日：2024-05-07
Applicant: ROLLS-ROYCE plc
Inventor： Craig W. BEMMENT , Alastair G. Hobday , Benjamin J. Keeler , Andrea Minelli , Andrew T. Smith , Martin K. Yates
CPC classification number: F02C7/224 , F02C7/14 , F02C7/32 , F05D2260/20
Abstract: A method of operating a gas turbine engine having an engine core having a 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 gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft; a heat exchange system having at least one fuel-oil heat exchanger arranged to transfer heat to the fuel; and a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located downstream of the at least one fuel-oil heat exchanger. The method comprises controlling the heat exchange system so as 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：US20240209788A1
公开(公告)日：2024-06-27
申请号：US18337699
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: F02C7/224 , F02C7/222 , F02C7/232 , F05D2270/07
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 raise the fuel temperature to an average of at least 135° C. on entry to the combustor at cruise conditions. Also provided is a gas turbine for an aircraft.
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公开(公告)号：US20240209785A1
公开(公告)日：2024-06-27
申请号：US18337497
申请日：2023-06-20
Applicant: ROLLS-ROYCE plc
Inventor： Craig W. BEMMENT , Alastair G. HOBDAY , Benjamin J. KEELER , Andrea MINELLI , Andrew T. SMITH , Martin K. YATES
CPC classification number: F02C7/224 , F02C7/14 , F02C7/32 , F23R3/005 , F05D2260/20
Abstract: A method of operating a gas turbine engine having an engine core having a 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 gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft; a heat exchange system having at least one fuel-oil heat exchanger arranged to transfer heat to the fuel; and a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located downstream of the at least one fuel-oil heat exchanger. The method includes operating the gas turbine engine using a fuel having a lubricity of between 0.71 mm and 0.90 mm wear scar diameter (WSD) at 25° C.
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公开(公告)号：US20230366356A1
公开(公告)日：2023-11-16
申请号：US18227648
申请日：2023-07-28
Applicant: ROLLS-ROYCE PLC
Inventor： Craig W. BEMMENT
Abstract: The present disclosure relates to a geared gas turbine engine for an aircraft. Example embodiments include a gas turbine engine for an aircraft including: an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan having a plurality of fan blades; and a gearbox that receives an input from the core shaft to drive the fan at a lower rotational speed than the core shaft, the gearbox having a gear ratio of around 3.4 or higher, wherein the gas turbine engine is configured such that a jet velocity ratio between a first jet velocity exiting from a bypass duct of the engine and a second jet velocity exiting from an exhaust nozzle of the engine core is within a range from around 0.75 to around 0.82.
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