-
公开(公告)号：US20180178920A1
公开(公告)日：2018-06-28
申请号：US15846994
申请日：2017-12-19
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.
-
公开(公告)号：US20150284101A1
公开(公告)日：2015-10-08
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 vapour 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 vapour 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 vapour 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。
-
公开(公告)号：US20150100219A1
公开(公告)日：2015-04-09
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 vapour trail detection sensor configured to generate a detection signal indicative of a characteristic of a vapour 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 vapour 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。
-
公开(公告)号：US20250059922A1
公开(公告)日：2025-02-20
申请号：US18936481
申请日：2024-11-04
Applicant: ROLLS-ROYCE PLC
Inventor： Peter SWANN , Craig W. BEMMENT , Christopher P. MADDEN
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.
-
公开(公告)号：US20250043715A1
公开(公告)日：2025-02-06
申请号：US18715858
申请日：2022-11-16
Applicant: ROLLS-ROYCE plc
Inventor： Chloe J PALMER , Peter SWANN
Abstract: A combined cycle power generation and storage system is shown. A liquid air energy storage system uses excess power to liquefy air and stores it in a liquid state. A combustion engine produces power by combustion of a carbon-based fuel along with an exhaust stream containing carbon dioxide. A heat recovery system exchanges heat from the exhaust stream to air from the liquid air storage system, and thereby produce a cooled exhaust stream and heated air. An air expansion machine recovers power by expansion of heated air from the heat recovery system. A separation system separates carbon dioxide from ambient air prior to liquefaction during operation of the liquid air energy storage system, and separates carbon dioxide from the cooled exhaust stream during operation of the combustion engine prior to emission of the cooled exhaust stream to atmosphere.
-
Patent Agency Ranking
公开(公告)号：US20240418133A1
公开(公告)日：2024-12-19
申请号：US18738784
申请日：2024-06-10
Applicant: ROLLS-ROYCE PLC
Inventor： Peter SWANN
Abstract: This invention concerns a fuel delivery system for an aircraft engine, comprising a fuel delivery regulator configured 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 configured to control operation of the regulator. The control unit is configured to actuate 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 a cruise phase relative to a further portion of an aircraft flight. The different fuels may comprise kerosene and an alternative fuel, such as a biofuel.
-
公开(公告)号：US20240418129A1
公开(公告)日：2024-12-19
申请号：US18421471
申请日：2024-01-24
Applicant: ROLLS-ROYCE PLC
Inventor： Christopher P MADDEN , Craig W BEMMRNT , Andrew T SMITH , Peter SWANN
Abstract: There is provided a method of operating a gas turbine engine including a combustor. The combustor includes a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the chamber. The nozzles include a first and second subset of fuel spray nozzles. The combustor is operable in a condition wherein the first subset is supplied with more fuel than the second. A ratio of the number of nozzles in the first subset to the second is 1:2 to 1:5. The method includes operating the engine so a reduction of 20-80% in an average of particles/kg of nvPM in the exhaust when the engine is operating at 85% available thrust for given operating conditions and when the engine is operating at 30% is obtained when fuel provided to the nozzles is a sustainable aviation fuel instead of a fossil-based hydrocarbon fuel. Also provided is a gas turbine engine for an aircraft.
-
公开(公告)号：US20240384689A1
公开(公告)日：2024-11-21
申请号：US18785965
申请日：2024-07-26
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN , Christopher P. Madden , Craig W. Bemment
Abstract: A aircraft gas turbine engine and operation method, the engine including: a staged combustion system having pilot and main fuel injectors, and operates in a pilot-only range wherein fuel delivers to pilot fuel injectors, and a pilot-and-main operation range wherein fuel is delivered to at least the main fuel injectors. The engine further includes a fuel delivery regulator to pilot and main fuel injectors, which receives fuel from a first and second source containing fuels each with different characteristics. The staged combustion system switches between pilot-only and pilot-and-main range operation when in steady cruise mode, the mode defining a boundary between first and second engine cruise operation range. The fuel delivery regulator delivers fuel to pilot fuel injectors during at least part of the first engine cruise operation with different fuel characteristics from fuel delivered to one or both pilot and main fuel injectors the second engine cruise operation range.
-
公开(公告)号：US20240352898A1
公开(公告)日：2024-10-24
申请号：US18755944
申请日：2024-06-27
Applicant: ROLLS-ROYCE plc
Inventor： Peter SWANN , Craig W. BEMMENT , Alastair G. HOBDAY , Benjamin J. KEELER , Christopher P. MADDEN
CPC classification number: F02C9/40 , F01D21/003 , F02C9/28 , F05D2220/323 , F05D2260/83 , F05D2270/07 , F05D2270/71
Abstract: A power system for an aircraft comprises a gas turbine engine, arranged to burn a fuel in a combustor so as to provide power to the aircraft; a plurality of fuel tanks arranged to contain fuel to be used to provide power to the aircraft; and a fuel manager. A first fuel tank of the plurality of fuel tanks is arranged to contain a first fuel, and a second tank of the plurality of fuel tanks is arranged to contain a second, different, 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 take fuel from the second tank for engine start-up, before switching to the first fuel tank.
-
公开(公告)号：US20240210037A1
公开(公告)日：2024-06-27
申请号：US18211624
申请日：2023-06-20
Applicant: ROLLS-ROYCE plc
Inventor： Christopher P MADDEN , Craig W BEMMENT , Andrew T SMITH , Peter SWANN
CPC classification number: F02C9/40 , F02C3/20 , F23R3/28 , F05D2240/35 , F05D2270/08
Abstract: A method of operating a gas turbine engine including a combustor. The combustor includes a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the chamber. The nozzles include a first and second subset of fuel spray nozzles. The combustor is operable in a condition wherein the first subset is supplied with more fuel than the second. A ratio of the number of nozzles in the first subset to the second is 1:2 to 1:5. The method includes operating the engine so a reduction of 20-80% in an average of particles/kg of nvPM in the exhaust when the engine is operating at 85% available thrust for given operating conditions and when the engine is operating at 30% is obtained when fuel provided to the nozzles is a sustainable aviation fuel instead of a fossil-based hydrocarbon fuel. Also, a gas turbine engine for an aircraft.
-
-
-
-
-
-
-
-
-
Search Results
75
records
(took 0.018 seconds)
