公开(公告)号：US20250003592A1

公开(公告)日：2025-01-02

申请号：US18882197

申请日：2024-09-11

Applicant: ROLLS-ROYCE plc

Inventor： Christopher P. MADDEN ,  Craig W BEMMENT ,  Andrew T SMITH ,  Peter SWANN

IPC: F23R3/28 ,  B64D27/10 ,  F02C7/264

Abstract: A method of operating a gas turbine engine; the gas turbine engine includes a combustor. The combustor includes a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber. The plurality of fuel spray nozzles includes 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 fuel to the one or more fuel-oil heat exchangers. Also provided is a gas turbine engine for an aircraft.

公开(公告)号：US20230323824A1

公开(公告)日：2023-10-12

申请号：US18098433

申请日：2023-01-18

Applicant: ROLLS-ROYCE PLC

Inventor： Peter SWANN ,  Christopher P MADDEN ,  Craig W BEMMENT

IPC: F02C9/40 ,  F02C9/28

CPC classification number: F02C9/40 ,  F02C9/28 ,  F05D2270/31 ,  F05D2220/323 ,  F05D2270/306 ,  F05D2220/80

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：US20230258137A1

公开(公告)日：2023-08-17

申请号：US18162970

申请日：2023-02-01

Applicant: ROLLS-ROYCE plc

Inventor： Peter SWANN

IPC: F02C9/40 ,  F02C7/22 ,  F02C9/28

CPC classification number: F02C9/40 ,  F02C7/22 ,  F02C9/28 ,  F05D2270/306 ,  F05D2270/3032 ,  F05D2220/32

Abstract: An engine system comprises a first fuel store, a second fuel store, an engine arranged to produce mechanical power by combustion or oxidation of a fuel in an engine, a fuel distribution system arranged to deliver fuel from the first and second fuel stores to the engine, the first fuel delivered at a first mass flow rate, the second fuel delivered at a second mass flow rate, the first and second mass flow rates contributing to a total mass flow rate of fuel to the engine; and a control system arranged to control the relative fractions of the total mass flow rate of fuel to the engine represented by the first mass flow rate and the second mass flow rate, based on an engine temperature.

公开(公告)号：US20230193838A1

公开(公告)日：2023-06-22

申请号：US18084083

申请日：2022-12-19

Applicant: ROLLS-ROYCE plc

Inventor： Peter SWANN ,  Craig W. BEMMENT ,  Alastair G. HOBDAY ,  Benjamin J. KEELER ,  Christopher P. MADDEN

IPC: F02C9/40 ,  F01D21/00 ,  F02C9/28

CPC classification number: F02C9/40 ,  F01D21/003 ,  F02C9/28 ,  F05D2220/323 ,  F05D2260/83 ,  F05D2270/07 ,  F05D2270/71

Abstract: A method of operating an aircraft that includes a propulsion system. The propulsion system includes 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 controlling the propulsion system based on the at least one fuel characteristic.

公开(公告)号：US20230101578A1

公开(公告)日：2023-03-30

申请号：US17941374

申请日：2022-09-09

Applicant: ROLLS-ROYCE PLC

Inventor： Peter SWANN ,  Kevin M BRITCHFORD

IPC: B64D27/10 ,  B64D27/24 ,  B64D31/00 ,  F02C6/00

Abstract: An aircraft hybrid propulsion system (5) comprising an inboard gas turbine engine (10a, 10c) and an outboard gas turbine engine (10b, 10d), each comprising a propulsor (12a, 12b) and a respective electric machine (32a, 32b) coupled to one or more engine shaft (24a, 24b). An electrical interconnection (34) is provided between the electric machine (32a) of the inboard gas turbine engine (10a) and the electric machine (32b) of the outboard gas turbine engine (10b). A controller (36) is configured to transfer electrical power between the inboard gas turbine engine electrical machine and the outboard gas turbine engine electrical machine when a thrust setting change is selected.

公开(公告)号：US20160376918A1

公开(公告)日：2016-12-29

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 ,  B64D27/18 ,  F02K3/06 ,  B64D27/24 ,  F02C3/04 ,  F02C7/22

CPC classification number: F01D21/003 ,  B64C21/025 ,  B64C23/065 ,  B64D27/18 ,  B64D27/24 ,  B64D2027/026 ,  F01D15/10 ,  F01D17/24 ,  F02C3/04 ,  F02C7/22 ,  F02K3/06 ,  F02K3/075 ,  F05D2220/323 ,  F05D2260/42 ,  F05D2270/306

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 vapour 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.

Abstract translation: 本发明涉及一种具有发动机芯的飞行器推进系统，其中燃料被燃烧以产生包含由燃料燃烧产生的水的排气，至少一个推进风扇，用于产生与发动机芯的排气混合的大量空气流 以及一个或多个传感器，其被布置成感测通过来自发动机的排气流指示蒸气轨道形成的状况; 以及控制器，其布置成控制排气中的水质量流与由推进风扇推进的空气的质量流量的比率，使得在通过一个或多个传感器感测到所述条件时，比率减小。

公开(公告)号：US20160172865A1

公开(公告)日：2016-06-16

申请号：US14942104

申请日：2015-11-16

Applicant: ROLLS-ROYCE PLC

Inventor： Peter SWANN ,  Armin STRANJAK

IPC: H02J3/46 ,  G05B15/02

CPC classification number: H02J3/46 ,  G05B15/02 ,  G06Q50/06 ,  H02J3/381

Abstract: This invention concerns a method and apparatus for coordinating energy distribution over a local energy network having at least one generator and a plurality of systems requiring an energy supply for operation, each system in the local network being connected to the at least one generator and/or another system in the network for distribution of energy there-between. An agent for each respective one of the generator and systems has a data store, a data processor and a data transmitter and receiver for transmission and receipt of data communication with one or more of the other agents. The data processor of each agent is programmed to recognise a predetermined communication sequence having a plurality of ordered data communication steps required to initiate supply of energy between the generator or system of said agent and the generator or system associated with another agent. Each communication sequence is assigned a future time period for which the energy supply is to be enacted.

Abstract translation: 本发明涉及一种用于协调能量分配的方法和装置，该局部能量网络具有至少一个发生器和多个需要能量供给操作的系统，该局部网络中的每个系统连接至该至少一个发生器和/或 网络中的另一个系统，用于分配能源。 发电机和系统中的每个相应一个的代理具有数据存储器，数据处理器和用于传输和接收与一个或多个其他代理程序的数据通信的数据发送器和接收器。 每个代理的数据处理器被编程为识别具有在所述代理的发电机或系统与与另一个代理相关的发电机或系统之间启动能量供应所需的多个有序数据通信步骤的预定通信序列。 为每个通信序列分配能量供应将来的时间段。

公开(公告)号：US20150285158A1

公开(公告)日：2015-10-08

申请号：US14644799

申请日：2015-03-11

Applicant: ROLLS-ROYCE PLC

Inventor： Malcolm HILLEL ,  Peter SWANN ,  Andrew Martin ROLT ,  Paul FLETCHER

IPC: F02C9/20 ,  B64D31/06 ,  B64D33/04 ,  F02K1/76

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 vapour 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.

Abstract translation: 本发明涉及一种飞机推进控制系统，其中燃气涡轮发动机具有用于控制流向或来自发动机的一部分的流动的可启动流动开口。 一个或多个传感器被布置成通过来自发动机的排气流感测指示蒸气轨道形成的状况。 控制器被布置成控制流动开口的致动，以便在通过一个或多个传感器检测到所述状态时降低发动机的效率。 在一个示例中，流动开口是可变区域风扇喷嘴。

公开(公告)号：US20150134151A1

公开(公告)日：2015-05-14

申请号：US14526789

申请日：2014-10-29

Applicant: ROLLS-ROYCE PLC

Inventor： Peter SWANN

IPC: B64D37/30 ,  B64D45/00

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。

公开(公告)号：US20130340834A1

公开(公告)日：2013-12-26

申请号：US13896793

申请日：2013-05-17

Applicant: ROLLS-ROYCE PLC

Inventor： Peter SWANN

IPC: G05D7/06

CPC classification number: G05D7/0617 ,  F02C3/30 ,  F02C9/40 ,  F05D2270/08 ,  F05D2270/081 ,  F05D2270/0831 ,  F05D2270/804 ,  Y02T50/671 ,  Y02T50/677 ,  Y02T50/678 ,  Y10T137/0324

Abstract: A method includes i) identifying a period of operation corresponding to a fuel supply requirement; ii) determining at least one ambient air condition in which the machine will operate during the period; iii) determining a duration of time in which, whilst in the ambient air condition, it is required to achieve a predetermined vapour trail characteristic; iv) determining a resultant fuel composition for use by the machine in the ambient air condition to achieve the characteristic, where the resultant fuel composition includes at least one of the first and second fuel compositions; v) determining the ratio of at least the first and second fuel compositions required for sufficient resultant fuel composition for the duration of time determined in step iii); and vi) producing a first signal indicative of the ratio of at least the first and second fuel compositions required for the duration of time determined in step iii).

Abstract translation: 一种方法包括：i）识别对应于燃料供应要求的操作周期; ii）确定在该期间机器将运行的至少一个环境空气状况; iii）确定持续时间，其中在环境空气条件下，需要实现预定的蒸气踪迹特征; iv）确定所述机器在环境空气条件下使用的所得燃料组合物以达到所述特性，其中所得燃料组合物包括所述第一和第二燃料组合物中的至少一种; v）确定在步骤iii）中确定的持续时间内足够的所得燃料组合物所需的至少第一和第二燃料组合物的比例; 和vi）产生指示在步骤iii）中确定的持续时间所需的至少第一和第二燃料组合物的比率的第一信号。