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公开(公告)号：US20150107261A1
公开(公告)日：2015-04-23
申请号：US14493792
申请日：2014-09-23
Applicant: ROLLS-ROYCE PLC
Inventor： Thierry MOES , Rory Douglas STIEGER , Malcolm Laurence HILLEL , Parag VYAS
CPC classification number: B64D13/06 , B64D13/08 , B64D41/00 , B64D2013/0618 , B64D2013/0648 , Y02T50/56
Abstract: A bleed air system for an aircraft has a gas turbine engine and operating method. The system includes an environmental control system (ECS) for providing cabin airflow to the aircraft, including operating modes such as first and second air cycle machine operating modes and heat exchanger operating modes. The ECS includes first, second and third bleed ports each configured to provide engine bleed air from gas turbine engine compressors to the ECS. The ECS includes a bleed air system sensor arrangement configured to sense one or more bleed air system conditions, an environmental control system controller that selects an environmental control system operating mode that provides required cabin air flow and temperature at an optimal specific fuel consumption of the gas turbine engine at the sensed system conditions, and a bleed port valve controller which determines an operating pressure required to operate the environmental control system in the selected mode.
Abstract translation: 用于飞行器的排气系统具有燃气涡轮发动机和操作方法。 该系统包括用于向飞机提供机舱气流的环境控制系统（ECS），包括诸如第一和第二空气循环机操作模式和热交换器操作模式的操作模式。 ECS包括第一，第二和第三排放口，每个排放端口被配置为将燃气涡轮发动机压缩机的引擎排放空气提供给ECS。 ECS包括被配置为感测一个或多个排气系统条件的排气系统传感器装置，环境控制系统控制器，其选择环境控制系统操作模式，其提供在气体的最佳特定燃料消耗下所需的舱室空气流量和温度 涡轮发动机，以及排气口阀控制器，其确定在所选模式下操作环境控制系统所需的操作压力。
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公开(公告)号：US20150159499A1
公开(公告)日：2015-06-11
申请号：US14537382
申请日：2014-11-10
Applicant: ROLLS-ROYCE PLC
Inventor： Marko BACIC , Glenn Alexander KNIGHT , Parag VYAS , Sean Patrick ELLIS
CPC classification number: F01D11/14 , F01D11/20 , F02C9/00 , F02C9/28 , F05D2270/02 , F05D2270/04 , F05D2270/051 , F05D2270/20 , F05D2270/309 , F05D2270/44
Abstract: A thrust demand signal is provided to a processor of a gas turbine engine and is modified, according to growth time constants of a rotor and/or a casing of the engine, in order to control the rotational speed or the rate of change of rotational speed of the engine so as to prevent contact between the rotor and the casing.
Abstract translation: 推力需求信号被提供给燃气涡轮发动机的处理器，并且根据发动机的转子和/或壳体的生长时间常数被修改，以便控制转速或转速变化率 以防止转子和壳体之间的接触。
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Patent Agency Ranking
公开(公告)号：US20160207639A1
公开(公告)日：2016-07-21
申请号：US14964143
申请日：2015-12-09
Applicant: ROLLS-ROYCE PLC
Inventor： Sean ELLIS , Parag VYAS , Richardson NNAEKEZIE , Matthew MOXON , Ekin INCELEME
CPC classification number: B64D45/00 , B64D2045/0085 , B64F5/60 , G05B23/0283 , G06Q10/0635 , G06Q10/0875 , G06Q10/20 , G07C5/006 , G07C5/008 , G07C5/0808 , G07C5/085
Abstract: A computerised aircraft engine maintenance planning system for maintaining an aircraft engine fleet comprising a plurality of aircraft engines, each engine in the fleet comprising an engine health monitoring system configured to provide data indicative of an incipient fault for a respective engine. The planning system comprises: a fault forwarding sub-system configured to receive indications of incipient faults from respective engine health monitoring systems, the fault forwarding system being configured to identify two or more engines having linked incipient faults; and a queuing sub-system configured to assign each engine identified as having an incipient fault to a virtual maintenance queue position; wherein the queuing sub-system is configured to group engines having linked incipient faults to adjacent queue positions.
Abstract translation: 一种用于维护包括多个飞机发动机的飞机发动机机组的计算机化飞行器发动机维护计划系统，所述机队中的每个发动机包括发动机健康监测系统，所述发动机健康监测系统被配置为提供指示相应发动机的初始故障的数据。 所述规划系统包括：故障转发子系统，被配置为从各个发动机健康监控系统接收初始故障的指示，所述故障转发系统被配置为识别具有连接的初始故障的两个或多个引擎; 以及排队子系统，被配置为将被识别为具有初始故障的每个引擎分配给虚拟维护队列位置; 其中所述排队子系统被配置为将具有链接的初始故障的引擎分组到相邻队列位置。
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公开(公告)号：US20140333126A1
公开(公告)日：2014-11-13
申请号：US14069881
申请日：2013-11-01
Applicant: ROLLS-ROYCE PLC
Inventor： Parag VYAS
CPC classification number: B60R16/03 , B64D2221/00 , H02J3/46 , H02J4/00
Abstract: This invention relates to an electrical system for an aircraft, comprising: a first main generator connected to at least one load via a first bus; a second main generator connected to at least one load via a second bus; a first and a second auxiliary generator associated with the first and second buses, the auxiliary generators being driven by a common prime mover.
Abstract translation: 本发明涉及一种用于飞机的电气系统，包括：通过第一总线连接到至少一个负载的第一主发电机; 经由第二总线连接到至少一个负载的第二主发电机; 与第一和第二总线相关联的第一和第二辅助发电机，辅助发电机由公共原动机驱动。
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公开(公告)号：US20190309997A1
公开(公告)日：2019-10-10
申请号：US16311569
申请日：2017-07-10
Applicant: ROLLS-ROYCE PLC
Inventor： Paul FLETCHER , Parag VYAS , Robert D COLLINS , Chloe J PALMER , Stephen G BROWN
Abstract: A combined refrigeration and power plant. The power plant comprises an internal combustion engine an air cycle machine refrigerator driven by the internal combustion engine and configured to refrigerate atmospheric air to provide working fluid to combined refrigeration and power generation cycle, a refrigerated air storage unit configured to store working fluid produced by the air cycle machine refrigerator; and first and second heat exchangers. The first heat exchanger arrangement is configured to exchange heat between a device to be cooled and the working fluid, and the second heat exchanger arrangement is configured to exchange heat between the working fluid downstream of the first heat exchanger in the combined refrigeration and power generation cycle and waste heat from the internal combustion engine; and a generator turbine configured to receive heated working fluid from the second heat exchanger arrangement, and configured to power an electrical generator.
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公开(公告)号：US20160185462A1
公开(公告)日：2016-06-30
申请号：US14247708
申请日：2014-04-08
Applicant: ROLLS-ROYCE PLC
Inventor： Huw Llewellyn EDWARDS , Parag VYAS
IPC: B64D41/00 , H02P29/028 , B64D45/00
CPC classification number: B65D41/00 , B64D41/00 , B64D45/00 , B64D2221/00 , H02P25/22 , H02P29/0243 , H02P29/028 , H02P29/032
Abstract: A method of controlling an aircraft electrical system (40). The electrical system (40) comprises an alternating current electrical machine (56, 58) comprising a plurality of phases, each phase having a power rating, the electrical machine (56, 58) being configured to operate on failure of one or more phases. The method comprises: determining a power requirement; sensing a fault of one or more phases of the electrical machine (56, 58), and controlling the electrical machine (56, 58) to operate in a fault condition, in which the remaining phases of the electrical machine (56, 58) provide the electrical power requirement; and providing an overrating signal to a flight computer (66) of the aircraft (2) where the power provided by each phase exceeds the power rating of the respective phase.
Abstract translation: 一种控制飞机电气系统（40）的方法。 电气系统（40）包括包括多个相的交流电机（56,58），每个相具有额定功率，电机（56,58）被配置为在一个或多个相的故障下操作。 该方法包括：确定功率需求; 感测电机（56,58）的一个或多个相的故障，以及控制电机（56,58）在故障状态下工作，其中电机（56,58）的其余相提供 电力要求; 以及向所述飞行器（2）的飞行计算机（66）提供过分信号，其中由每个相位提供的功率超过相位的额定功率。
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公开(公告)号：US20140125121A1
公开(公告)日：2014-05-08
申请号：US14036721
申请日：2013-09-25
Applicant: ROLLS-ROYCE PLC
Inventor： Huw Llewelyn EDWARDS , Parag VYAS , Malcolm Laurence HILLEL , Alasdair GARDNER , Sean Patrick ELLIS , Nicholas HOWARTH
IPC: B60R16/03
CPC classification number: B60R16/03 , B64D2221/00 , H02J4/00 , H02J7/1446 , Y02T50/54
Abstract: A method of operating an electrical power generation system on an aircraft. The method includes assessing a required electrical power of the aircraft, assessing whether a first and a second electrical power source are able to provide the required electrical power in combination, assessing a predetermined condition, determining an operating mode of the first and second electrical power sources to match the predetermined condition, and operating the first and second electrical power sources according to the determined operating mode.
Abstract translation: 一种在飞机上操作发电系统的方法。 该方法包括评估飞行器的所需电力，评估第一和第二电源是否能够组合提供所需的电力，评估预定条件，确定第一和第二电源的操作模式 以匹配预定条件，并且根据所确定的操作模式操作第一和第二电源。
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