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公开(公告)号：US20230116146A1
公开(公告)日：2023-04-13
申请号：US18053124
申请日：2022-11-07
Applicant: ROLLS-ROYCE plc
Inventor： Christopher P. MADDEN , Peter SWANN
Abstract: 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：US20210277835A1
公开(公告)日：2021-09-09
申请号：US17189650
申请日：2021-03-02
Applicant: ROLLS-ROYCE plc
Inventor： Christopher P. MADDEN , Peter SWANN
IPC: F02C9/26
Abstract: 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：US20160304211A1
公开(公告)日：2016-10-20
申请号：US15079273
申请日：2016-03-24
Applicant: ROLLS-ROYCE PLC
Inventor： Peter SWANN
CPC classification number: B64D31/06 , B64D27/24 , B64D2027/026 , Y02T50/44 , Y02T50/62
Abstract: An aircraft propulsion system in which a combustion engine is arranged to drive an electrical generator. An electrical energy store is provided within the system. A propulsive rotor is arranged to be driven by an electric motor and a controller selectively varies the supply of power to the electric motor from the generator and/or energy store in dependence on one or more property of a vapour trail resulting from the engine exhaust flow. The controller may also control the supply of power to the energy store for charging.
Abstract translation: 一种其中内燃机布置成驱动发电机的飞行器推进系统。 在系统内提供电能存储。 推进式转子被布置成由电动机驱动，并且控制器根据发动机排气流产生的蒸气轨迹的一个或多个特性来选择性地改变来自发电机和/或能量存储器的电动机供电功率 。 控制器还可以控制向能量存储器供电以进行充电。
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公开(公告)号：US20160146117A1
公开(公告)日：2016-05-26
申请号：US14926928
申请日：2015-10-29
Applicant: ROLLS-ROYCE PLC
Inventor： Peter SWANN
CPC classification number: F02C9/40 , B64D37/04 , B64D37/28 , F02C7/22 , F02C7/232 , F02C9/46 , Y02T50/671
Abstract: This invention concerns fuel delivery system for an aircraft engine (10). The system entails two or more fuel sources (32, 34, 36) onboard an aircraft (54), each fuel source (32, 34, 36) having a different fuel therein. At least one fuel delivery regulator (30; 42; 44; 46) is arranged to receive fuel from the fuel sources onboard the aircraft for supply to the aircraft engine (10), and a control unit (26) arranged to control operation of the regulator (30; 42; 44; 46), wherein the control unit (26) actuates the regulator (30; 42; 44; 46) so as to vary the flow of fuels from the plurality of fuel sources to the engine (10) in an order of priority according to the specific energy of the different fuels in the plurality of fuel sources (32; 34; 36). The system may achieve fuel efficiency savings by burning the available fuels in a default priority order.
Abstract translation: 本发明涉及用于飞机发动机（10）的燃料输送系统。 该系统需要飞机（54）上的两个或更多个燃料源（32,34,36），每个燃料源（32,34,36）在其中具有不同的燃料。 至少一个燃料输送调节器（30; 42; 44; 46）布置成从飞行器上的燃料源接收燃料以供应到飞机发动机（10）;以及控制单元（26），其被布置成控制 调节器（30; 42; 44; 46），其中控制单元（26）致动调节器（30; 42; 44; 46），以便改变燃料从多个燃料源到发动机（10） 按照多个燃料源（32; 34; 36）中不同燃料的比能量的优先次序。 该系统可以通过以默认优先级顺序燃烧可用燃料来节省燃料消耗。
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公开(公告)号：US20150284102A1
公开(公告)日：2015-10-08
申请号：US14674823
申请日：2015-03-31
Applicant: ROLLS-ROYCE PLC
Inventor： Peter SWANN
CPC classification number: B64D31/06 , B64D33/04 , F02C9/16 , F05D2270/0831 , Y02T50/677
Abstract: The invention concerns an aircraft propulsion control system for an aircraft with a plurality of gas turbine engines mounted at different spaced positions relative to an airframe. One or more sensor is arranged to sense a condition indicative of vapour trail formation by an exhaust flow from one or more of the plurality of engines. A controller is arranged to be responsive to thrust demand for the aircraft and selectively to control each of the engines so as to modify the exhaust flow of at least one engine relative to at least one further engine according to the positions of the engines on the airframe. The proximity of an engine to a vortical wake flow created by the airframe may be used to determine suitable exhaust flow modifications. The controller may output a separate throttle control signal to each engine and/or may adjust the fuel composition supplied to each engine.
Abstract translation: 本发明涉及一种用于具有多个燃气涡轮发动机的飞机的飞行器推进控制系统，其安装在相对于机身的不同间隔位置处。 一个或多个传感器布置成通过来自多个发动机中的一个或多个的排气流感测指示蒸气轨迹形成的状况。 控制器被布置成响应于飞机的推力需求并且选择性地控制每个发动机，以便根据发动机在机身上的位置来修改至少一个发动机相对于至少一个另外的发动机的排气流 。 发动机与机身产生的涡流尾流的接近可用于确定合适的排气流修改。 控制器可以向每个发动机输出单独的节气门控制信号和/或可以调节供应给每个发动机的燃料组成。
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Patent Agency Ranking
公开(公告)号：US20130343958A1
公开(公告)日：2013-12-26
申请号：US13896690
申请日：2013-05-17
Applicant: ROLLS-ROYCE PLC
Inventor： Peter SWANN
CPC classification number: G01N33/0004 , F02C3/30 , F02C9/00 , F02C9/28 , F02C9/40 , F05D2270/08 , F05D2270/081 , F05D2270/0831 , F05D2270/804 , Y02T50/671 , Y02T50/677
Abstract: A fuel system (12) comprising a vapour trail detection sensor (20) configured to generate a first signal (28) which indicates the optical depth of a vapour trail (35). A control unit (40) is provided responsive to the first signal (28) and configured to generate a second signal (80) in dependence upon the first signal (28). The second signal (80) defines a percentage of at least one of a first fuel composition and second fuel composition required to produce a resultant fuel composition. At least one regulator (42) is provided configured to receive and be responsive to the second signal (80) and regulate the percentage of first and second fuel composition required to produce the resultant fuel composition.
Abstract translation: 一种燃料系统（12），包括蒸气跟踪检测传感器（20），其被配置为产生指示蒸气轨迹（35）的光学深度的第一信号（28）。 响应于第一信号（28）提供控制单元（40），并且被配置为根据第一信号（28）产生第二信号（80）。 第二信号（80）限定了产生所得燃料组合物所需的第一燃料组合物和第二燃料组合物中的至少一种的百分比。 提供至少一个调节器（42），其配置成接收并响应于第二信号（80）并且调节产生所得燃料组合物所需的第一和第二燃料组合物的百分比。
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公开(公告)号：US20240210039A1
公开(公告)日：2024-06-27
申请号：US18337477
申请日：2023-06-20
Applicant: ROLLS-ROYCE PLC
Inventor： Christopher P MADDEN , David M BEAVEN , Craig W BEMMENT , Paul W FERRA , Barani P GUNASEKARAN , Benjamin J KEELER , Peter SWANN , Martin K YATES
CPC classification number: F23R3/346 , F02C7/22 , F23K5/08 , F05D2240/35 , F23K2300/204
Abstract: There is provided a method of operating a gas turbine engine. The gas turbine engine comprises a staged combustor having an arrangement of fuel spray nozzles in which fuel flow is biased to a subset of the nozzles adjacent one or more ignitors during a re-light procedure. The method comprises transferring heat from the oil to the fuel before the fuel enters the combustor so as to lower the fuel viscosity to 0.58 mm2/s or lower on entry to the combustor at cruise conditions. Also disclosed is a gas turbine engine.
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公开(公告)号：US20240210038A1
公开(公告)日：2024-06-27
申请号：US18211793
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: F23R3/346 , F02C7/224 , F23K5/08 , F23K2300/204
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 lower the fuel viscosity to 0.58 mm2/s or lower on entry to the combustor at cruise conditions.
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公开(公告)号：US20240209800A1
公开(公告)日：2024-06-27
申请号：US18337531
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
Abstract: Provided is a method of operating a gas turbine engine. The engine includes a combustor having a plurality of fuel spray nozzles and a fuel system arranged to provide fuel to the combustor. The system includes: fuel pump; fuel distributing valve downstream of the pump arranged to distribute fuel to the plurality of nozzles and bias fuel flow to the nozzles such that a first subset of the plurality of nozzles receives more fuel than a second subset of the plurality of nozzles; and fuel-oil heat exchanger. The method includes providing a fuel to the combustor and transferring heat from oil to the fuel in the fuel-oil heat exchanger before the fuel enters the combustor so as to lower a viscosity of the fuel to 0.58 mm2/s or lower on entry to the combustor at cruise conditions. Also provided is a gas turbine engine for an aircraft.
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公开(公告)号：US20230366357A1
公开(公告)日：2023-11-16
申请号：US18225427
申请日：2023-07-24
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN , Christopher P. MADDEN , Craig W. BEMMENT
CPC classification number: F02C9/40 , F02C9/28 , F05D2270/08 , F05D2270/71 , F05D2270/31 , F05D2220/323 , F05D2270/306
Abstract: An aircraft has first and second fuel sources containing fuels with different characteristics, and one or more gas turbine engines powered by the fuels and each having a staged combustion system having pilot and main fuel injectors and being operable in pilot-only and pilot-and-main ranges of operation. The gas turbine engines each have a fuel delivery regulator arranged to control fuel delivery to the pilot and main fuel injectors. The method includes: obtaining a proposed mission description; obtaining nvPM impact parameters for the gas turbine engines, the impact parameters being associated with each operating condition of the proposed mission; calculating an optimised set of one or more fuel characteristics for each flight condition of the proposed flight defined in the flight description based on the nvPM impact parameters; and determining a fuel allocation based on the optimised set of one or more fuel characteristics.
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