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公开(公告)号：US12098679B2
公开(公告)日：2024-09-24
申请号：US18337615
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
Abstract: There is provided a method of operating a gas turbine engine. The gas turbine engine comprises a staged combustor comprising 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 providing fuel to the combustor having a calorific value of at least 43.5 MJ/kg. Also disclosed is a gas turbine engine.
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公开(公告)号：US11988144B2
公开(公告)日：2024-05-21
申请号：US18337516
申请日：2023-06-20
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: F02C7/14 , F02C7/224 , F02C7/36 , F05D2220/323 , F05D2260/213
Abstract: 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：US11965467B2
公开(公告)日：2024-04-23
申请号：US17941358
申请日：2022-09-09
Applicant: ROLLS-ROYCE plc
Inventor： Peter Swann , Kevin M Britchford
CPC classification number: F02C9/42 , F02C9/28 , B64D2027/026 , F05D2220/323 , F05D2270/051 , F05D2270/053 , F05D2270/333 , F05D2270/335 , F05D2270/71
Abstract: An aircraft propulsion system comprises first and second thrust producing gas turbine engines. The system comprises a controller configured to determine a required overall propulsion system thrust level, and determine an engine core power level contribution from each aircraft gas turbine engine such that the overall propulsion system produces a minimum overall noise level and meets the required overall propulsion system thrust level. In meeting the minimum overall noise level, at least the first and second gas turbine engines are operated at different engine core power settings.
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公开(公告)号：US11754001B2
公开(公告)日：2023-09-12
申请号：US17444133
申请日：2021-07-30
Applicant: ROLLS-ROYCE plc
Inventor： Peter Swann
CPC classification number: F02C7/36 , F02C6/20 , F02C9/00 , F05D2220/323 , F05D2220/76 , F05D2270/01
Abstract: A control system for an aircraft hybrid propulsion system comprising a gas turbine engine coupled to an electric generator, a propulsor coupled to an electric motor, and an electrical storage device coupled to the motor and the generator. The control system configured to operate the propulsion system in a first descent mode and a second descent mode. In the first descent mode, the gas turbine engine is operated at a first engine power level and the generator is operated at a first generator power level. In the second descent mode, the gas turbine engine is operated at a second engine power level, higher than the first engine power level, and the generator is operated at a second generator power level, higher than the first generator power level. Electric power generated by the electric generator during operation in the second descent mode is stored in the electrical storage device.
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公开(公告)号：US11260983B2
公开(公告)日：2022-03-01
申请号：US16552433
申请日：2019-08-27
Applicant: Rolls-Royce plc
Inventor： Peter Swann , Paul Fletcher , Alvise Pellegrini , Ashog Kulathasan
Abstract: This invention concerns an aircraft propulsion system in which an engine has an engine core comprising a compressor, a combustor and a turbine driven by a flow of combustion products of the combustor. At least one propulsive fan generates a mass flow of air to propel the aircraft. An electrical energy store is provided on board the aircraft. At least one electric motor is arranged to drive the propulsive fan and the engine core compressor. A controller controls the at least one electric motor to mitigate the creation of a contrail caused by the engine combustion products by altering the ratio of the mass flow of air by the propulsive fan to the flow of combustion products of the combustor. The at least one electric motor is controlled so as to selectively drive both the propulsive fan and engine core compressor.
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Patent Agency Ranking
公开(公告)号：US09896218B2
公开(公告)日：2018-02-20
申请号：US14644993
申请日：2015-03-11
Applicant: ROLLS-ROYCE PLC
Inventor： Peter Swann
CPC classification number: B64D31/10 , F02C9/00 , F02C9/42 , F05D2220/323 , F05D2270/051 , F05D2270/08 , F05D2270/0831 , F05D2270/13 , F05D2270/335 , Y02T50/671 , Y02T50/677
Abstract: The invention concerns an aircraft propulsion control system in which multiple gas turbine engines (10) are under the control of a controller (30). One or more sensor is arranged to sense a condition indicative of vapor trail formation by an exhaust flow from one or more of the engines. The controller (30) is arranged to be responsive to a thrust demand (51) for the aircraft and to control the thrust produced by each of the engines (10) concurrently so as to alter the efficiency of the engines upon sensing of the vapor trail formation condition, while satisfying the aircraft thrust demand. The controller (30) may output a separate throttle control signal (35) to each engine (10).
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公开(公告)号：US09650968B2
公开(公告)日：2017-05-16
申请号：US14486563
申请日：2014-09-15
Applicant: ROLLS-ROYCE PLC
Inventor： Peter Swann
CPC classification number: F02C9/28 , F02C3/20 , F02C7/22 , F02C9/26 , F02C9/40 , F05D2270/08 , F05D2270/311 , F05D2270/312 , F05D2270/313 , Y02T50/671 , Y02T50/677
Abstract: This invention concerns a method of delivering fuel to an aircraft engine 60, which involves providing a plurality of distinct fuel sources 20, 22, a first fuel source 20 comprising a first fuel having a first aromatic content and a second fuel source 22 comprising a second fuel having a second aromatic content. One or more ambient atmospheric condition is determined for at least a portion of a flight path of the aircraft, said condition being indicative of a likelihood of contrail 135 formation by the engine 60. A desirous fuel composition for combustion by the engine is determined based upon the one or more ambient atmospheric condition and a ratio of the first and second fuels from said respective fuel sources is selected according to said desirous fuel composition. The selected ratio of the first and second fuels is delivered to the aircraft engine 60.
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公开(公告)号：US09567101B2
公开(公告)日：2017-02-14
申请号：US14526789
申请日：2014-10-29
Applicant: ROLLS-ROYCE PLC
Inventor： Peter Swann
CPC classification number: B64D45/00 , B64D37/30 , F02C3/20 , F02C7/236 , F02C9/40 , F05D2270/07 , F05D2270/081 , Y02T50/671 , Y02T50/677 , Y02T50/678
Abstract: This invention concerns a fuel delivery system for an aircraft engine, including a fuel delivery regulator arranged to receive fuel from a plurality of fuel sources for supply to the engine. An engine operating condition sensor reading is received by a control unit arranged to control operation of the regulator. The control unit actuates the regulator based on a received signal from the engine operating condition sensor in order to vary the volume of fuels from the plurality of fuel sources supplied to the engine during at least a portion of the landing/take-off (LTO) cycle relative to a further portion of the aircraft flight. The different fuels may include kerosene and an alternative fuel, such as a biofuel.
Abstract translation: 本发明涉及一种用于飞行器发动机的燃料输送系统，其包括燃料输送调节器，燃料输送调节器布置成从多个燃料源接收燃料以供给发动机。 发动机操作条件传感器读数由布置成控制调节器的操作的控制单元接收。 控制单元基于来自发动机操作条件传感器的接收信号来致动调节器，以便在着陆/起飞（LTO）的至少一部分期间改变从提供给发动机的多个燃料源中的燃料的体积， 相对于飞机飞行的另一部分。 不同的燃料可以包括煤油和替代燃料，例如生物燃料。
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公开(公告)号：US09399521B2
公开(公告)日：2016-07-26
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 vapor 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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公开(公告)号：US09309811B2
公开(公告)日：2016-04-12
申请号：US14486337
申请日：2014-09-15
Applicant: ROLLS-ROYCE PLC
Inventor： Peter Swann
CPC classification number: F02C9/28 , F02C3/20 , F02C7/22 , F02C9/40 , F05D2270/081 , F05D2270/082 , G01N21/538 , Y02T50/671 , Y02T50/677
Abstract: This invention concerns a fuel delivery system for an engine, in which two or more discrete fuel compositions are made available to the engine. The system has a vapor trail detection sensor configured to generate a detection signal indicative of a characteristic of a vapor trail. A regulator is configured to regulate a percentage of a first and a second fuel composition delivered to the engine as resultant fuel composition. A controller is arranged to undertake a search of trial fuel compositions by controlling the regulator to deliver to the engine a plurality of trial fuel compositions having different ratios of the first and second fuel compositions. The controller controls delivery of a resultant fuel composition to the engine in response to the vapor trail characteristic detection signals for said plurality of trial fuel compositions.
Abstract translation: 本发明涉及用于发动机的燃料输送系统，其中两个或多个离散的燃料组合物可用于发动机。 该系统具有蒸气跟踪检测传感器，该传感器被配置为产生指示蒸气踪迹的特征的检测信号。 调节器构造成调节作为所得燃料组合物输送到发动机的第一和第二燃料组合物的百分比。 控制器被布置成通过控制调节器向发动机输送具有不同比例的第一和第二燃料组合物的多个试验燃料组合物来搜索试验燃料组合物。 控制器响应于所述多个试验燃料组合物的蒸气踪迹特性检测信号控制所得燃料组合物向发动机的输送。
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