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公开(公告)号：US20230332548A1
公开(公告)日：2023-10-19
申请号：US18208077
申请日：2023-06-09
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN , Craig W BEMMENT , Christopher P MADDEN
CPC classification number: F02C9/26 , B64D27/10 , F02C7/22 , B64D37/30 , F05D2220/323
Abstract: A gas turbine engine for an aircraft includes a staged combustion system having pilot fuel injectors and main fuel injectors. The gas turbine engine further includes a fuel delivery regulator arranged to control delivery of fuel to the pilot and main fuel injectors, and a fuel characteristic determination module configured to determine one or more fuel characteristics of the fuel being supplied to the staged combustion system. A controller is configured to determine a staging point defining the point at which the staged combustion system is switched between pilot-only operation and pilot-and-main operation, the staging point being determined based on the determined one or more fuel characteristics, the controller being configured to control the staged combustion system according to the determined staging point.
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公开(公告)号：US20230296060A1
公开(公告)日：2023-09-21
申请号：US18324619
申请日：2023-05-26
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN , Craig W BEMMENT , Alastair G HOBDAY , Benjamin J KEELER , Christopher P MADDEN
CPC classification number: F02C9/28 , B64D37/04 , G08G5/0034 , B64D27/10
Abstract: A method of operating an aircraft including a gas turbine engine and a plurality of fuel tanks arranged to provide fuel to the gas turbine engine. At least two of the fuel tanks contain fuels with different fuel characteristics. The method includes obtaining a flight profile for a portion of a flight of the aircraft; and determining a fueling schedule for the portion of the flight based on the flight profile and the fuel characteristics, the fueling schedule governing the variation with time of how much fuel is drawn from each tank. Fuel input to the gas turbine engine may then be controlled in operation in accordance with the fueling schedule.
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公开(公告)号：US20230127713A1
公开(公告)日：2023-04-27
申请号：US17870270
申请日：2022-07-21
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：US20220205386A1
公开(公告)日：2022-06-30
申请号：US17697630
申请日：2022-03-17
Applicant: ROLLS-ROYCE PLC
Inventor： Craig W BEMMENT , Pascal DUNNING
Abstract: A gas turbine engine for an aircraft comprises an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, wherein a compressor exit temperature is defined as an average temperature of airflow at the exit from the compressor; and a fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, each fan blade having a leading edge and a trailing edge, wherein a fan rotor entry temperature is defined as an average temperature of airflow across the leading edge of each fan blade at cruise conditions and a fan tip rotor exit temperature is defined as an average temperature of airflow across a radially outer portion of each fan blade at the trailing edge at cruise conditions. A core to fan tip temperature rise ratio is in the range from 2.845 to 3.8.
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公开(公告)号：US20200277901A1
公开(公告)日：2020-09-03
申请号：US16443942
申请日：2019-06-18
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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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：US20240191661A1
公开(公告)日：2024-06-13
申请号：US18439253
申请日：2024-02-12
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：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：US20240077036A1
公开(公告)日：2024-03-07
申请号：US18203993
申请日：2023-05-31
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN , Craig W BEMMENT , Alastair G HOBDAY , Benjamin J KEELER , Christopher P MADDEN
CPC classification number: F02C9/28 , B64D27/10 , B64D37/04 , G08G5/0034
Abstract: A method of operating an aircraft including a gas turbine engine and a fuel tank arranged to provide fuel to the gas turbine engine. The method includes: determining at least one fuel characteristic of the fuel arranged to be provided to the gas turbine engine; and proposing or initiating a change to a flight profile of the aircraft based on the at least one fuel characteristic. For example, intended route and/or altitude of the aircraft may be changed based on the one or more fuel characteristics.
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