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公开(公告)号：US10371003B2
公开(公告)日：2019-08-06
申请号：US15163318
申请日：2016-05-24
Applicant: ROLLS-ROYCE plc
Inventor： Peter Swann , Andrew M Rolt , Paul Fletcher
IPC: F01D21/00 , F02C3/04 , F02C7/22 , F02K3/06 , B64D27/24 , B64D27/18 , F02K3/075 , B64C21/02 , B64C23/06 , F01D15/10 , F01D17/24 , B64D27/02
Abstract: The invention concerns an aircraft propulsion system having an engine core within which fuel is combusted to produce an exhaust containing water produced from the combustion of fuel, at least one propulsive fan for generating a mass flow of air which mixes with the exhaust of the engine core, and one or more sensor arranged to sense a condition indicative of vapor trail formation by the exhaust flow from the engine; and a controller arranged to control the ratio of the mass flow of water in the exhaust to the mass flow of air propulsed by the propulsive fan such that the ratio is reduced upon sensing of said condition by the one or more sensor.
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公开(公告)号：US09739207B2
公开(公告)日：2017-08-22
申请号：US14644799
申请日：2015-03-11
Applicant: ROLLS-ROYCE PLC
Inventor： Malcolm Hillel , Peter Swann , Andrew Martin Rolt , Paul Fletcher
CPC classification number: F02C9/20 , B64D31/06 , B64D33/04 , F02K1/1207 , F02K1/16 , F02K1/76 , F02K1/825 , F02K3/075 , F05D2220/323 , F05D2270/08 , F05D2270/311 , F05D2270/312 , F05D2270/313 , Y02T50/677
Abstract: The invention concerns an aircraft propulsion control system in which a gas turbine engine has an actuable flow opening for control of flow to or from a portion of the engine. One or more sensor is arranged to sense a condition indicative of vapor trail formation by the exhaust flow from the engine. A controller is arranged to control actuation of the flow opening so as to reduce the efficiency of the engine upon sensing of said condition by the one or more sensor. In one example, the flow opening is a variable area fan nozzle.
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公开(公告)号：US09518965B2
公开(公告)日：2016-12-13
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 vapor trail detection sensor (20) configured to generate a first signal (28) which indicates the optical depth of a vapor 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：US09440746B2
公开(公告)日：2016-09-13
申请号：US14644874
申请日：2015-03-11
Applicant: ROLLS-ROYCE PLC
Inventor： Peter Swann
CPC classification number: B64D31/06 , B64D45/00 , B64D2045/0085 , B64D2045/009 , G05B17/02
Abstract: An aircraft propulsion control system for an aircraft having a plurality of combustion engines is provided. The system has a plurality of sensors for sensing a condition indicative of properties and/or formation of vapor trails which may be formed by the plurality of engines. A controller is arranged to control one or more operational variable for each of the plurality of engines. The controller is arranged to undertake a search of trial values of the operational variable by instructing different concurrent values of said operational variable across the plurality of engines and determining the resulting impact on the vapor trail formation and/or properties as sensed by the sensors. A population-based search may be performed, for example in parallel over all the engines at once so as to reduce the time taken to achieve vapor trail mitigation.
Abstract translation: 提供了一种具有多个内燃机的飞机的飞机推进控制系统。 该系统具有多个传感器，用于感测指示可由多个发动机形成的蒸汽气道的性质和/或形成的状况。 控制器被布置成控制多个发动机中的每一个的一个或多个操作变量。 控制器被布置成通过指示跨越多个发动机的所述操作变量的不同并行值来确定对由所述传感器感测的所述蒸气轨道形成和/或性质的所得影响，来对所述操作变量的试验值进行搜索。 可以例如在所有引擎上同时执行基于人群的搜索，以便减少实现蒸气跟踪缓解所花费的时间。
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公开(公告)号：US09146566B2
公开(公告)日：2015-09-29
申请号：US13896766
申请日：2013-05-17
Applicant: ROLLS-ROYCE PLC
Inventor： Peter Swann
CPC classification number: G05D11/132 , F02C3/30 , F02C7/22 , F02C9/40 , F05D2270/08 , F05D2270/081 , F05D2270/0831 , F05D2270/804 , Y02T50/671 , Y02T50/677
Abstract: A fuel system (10) comprising a fluid blender (14) in fluid communication with a source of a first fuel composition and a source of a second fuel composition via at least one inlet (32, 34). The blender (14) is operable to receive at least the first fuel composition and/or second fuel composition via the at least one inlet (32, 34), and output a resultant fuel composition comprising the received fuel compositions via at least one outlet (36). The at least one outlet (36) is in fluid communication with an engine fuel injection device (38).
Abstract translation: 一种燃料系统（10），包括通过至少一个入口（32,34）与第一燃料组合物的源和第二燃料组合物的源流体连通的流体搅拌器（14）。 搅拌器（14）可操作以经由至少一个入口（32,34）接收至少第一燃料组合物和/或第二燃料组合物，并且经由至少一个出口输出包含所接收的燃料组合物的所得燃料组合物（ 36）。 所述至少一个出口（36）与发动机燃料喷射装置（38）流体连通。
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Patent Agency Ranking
公开(公告)号：US12240614B2
公开(公告)日：2025-03-04
申请号：US18209136
申请日：2023-06-13
Applicant: ROLLS-ROYCE plc
Inventor： Peter Swann , Craig W Bemment , Alastair G Hobday , Benjamin J Keeler , Christopher P Madden
Abstract: A power system for an aircraft includes one or more gas turbine engines arranged to burn a fuel so as to provide power to the aircraft; a plurality of fuel tanks each arranged to contain a fuel to be used to provide power to the aircraft; and a fuel manager. At least two of the fuel tanks contain different fuels, which have different proportions of a sustainable aviation fuel. The fuel manager is arranged to store information on the fuel contained in each fuel tank; and to control fuel supply so as to select a specific fuel accordingly to power at least the majority of operations on the ground. The fuel manager may additionally identify which tank contains the fuel with the highest proportion of a sustainable aviation fuel; and that fuel may be used to power at least the majority of operations on the ground.
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公开(公告)号：US12180899B2
公开(公告)日：2024-12-31
申请号：US17853191
申请日：2022-06-29
Applicant: ROLLS-ROYCE plc
Inventor： Peter Swann , Craig W Bemment , Christopher P Madden
Abstract: A gas turbine engine for an aircraft, including: staged combustion system having pilot fuel injectors and main fuel injectors, staged combustion system being operable in pilot-only range of operation and pilot-and-main range of operation; and fuel delivery regulator arranged to control delivery of fuel to pilot and main fuel injectors. Fuel delivery regulator arranged to receive fuel from a first fuel source containing a first fuel having a first fuel characteristic and a second fuel source containing a second fuel having a different second fuel characteristic. The fuel delivery regulator is arranged to deliver fuel to the pilot fuel injectors during at least part of the pilot-only range of operation having a different fuel characteristic from fuel delivered to one or both of the pilot and main fuel injectors during at least part of the pilot-and-main range of operation. A method of operating a gas turbine engine is also disclosed.
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公开(公告)号：US12168958B2
公开(公告)日：2024-12-17
申请号：US18211809
申请日：2023-06-20
Applicant: ROLLS-ROYCE PLC
Inventor： Christopher P Madden , Craig W Bemment , Andrew T Smith , Peter Swann
Abstract: A method of operating a gas turbine engine having a combustor having a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber. The fuel spray nozzles have a first subset of fuel spray nozzles and a second subset of fuel spray nozzles. The combustor is operable in a condition in which the first subset of fuel spray nozzles are supplied with more fuel than the second subset of fuel spray nozzles. A ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:2 to 1:5. The method includes providing a fuel to the plurality of fuel spray nozzles having a calorific value of at least 43.5 MJ/kg. A gas turbine engine can be for an aircraft.
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公开(公告)号：US12152542B2
公开(公告)日：2024-11-26
申请号：US18328991
申请日：2023-06-05
Applicant: ROLLS-ROYCE plc
Inventor： Peter Swann , David M. Beaven , Craig W. Bemment , Alastair G. Hobday , Benjamin J. Keeler , Christopher P. Madden , Martin K. Yates
Abstract: The present application provides a method of determining one or more fuel characteristics of an aviation fuel suitable for powering a gas turbine engine of an aircraft. The method includes: passing UV-visual spectrum light through the fuel; measuring a transmittance parameter indicating the transmittance of light through the fuel; determining one or more fuel characteristics of the fuel based on the transmittance parameter; and communicating the one or more fuel characteristic to a control module of the gas turbine engine or the aircraft. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.
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公开(公告)号：US12123362B2
公开(公告)日：2024-10-22
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 , F23R3/343 , F05D2220/323 , F05D2270/08 , F05D2270/306 , F05D2270/31 , F05D2270/71
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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