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公开(公告)号：US20240327021A1
公开(公告)日：2024-10-03
申请号：US18602091
申请日：2024-03-12
Applicant: ROLLS-ROYCE plc
Inventor： Matthew MOXON
Abstract: An aircraft includes a fuselage and a wing, at least one hydrogen fuel tank and a fuel line configured to delivery fuel from the fuel tank to the engine. The fuel tank is installed externally of the fuselage and wing, and comprises an external aeroshell containing a plurality of pressure vessels configured to contain pressurised fuel therein.
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公开(公告)号：US20200047871A1
公开(公告)日：2020-02-13
申请号：US16658432
申请日：2019-10-21
Applicant: ROLLS-ROYCE plc
Inventor： Matthew MOXON
Abstract: An aircraft has an internal combustion engine and a wing including a hollow structural member. The aircraft has an electrical network including: an electrical motor configured to drive an aircraft propulsor; at least one conductor configured to electrically couple the electrical motor and an electrical storage device; wherein the electrical conductor is formed of the hollow structural member of the aircraft wing.
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公开(公告)号：US20180237126A1
公开(公告)日：2018-08-23
申请号：US15899481
申请日：2018-02-20
Applicant: ROLLS-ROYCE plc
Inventor： Martin N. GOODHAND , Matthew MOXON
Abstract: A boundary layer propulsor comprises a rotor and a plurality of first aerofoil blades. The rotor has an axis of rotation. The plurality of first aerofoil blades extends radially from the rotor and is arranged in a circumferential array around the axis of rotation. Each of the first aerofoil blades has, in a radially outward sequence, a radially proximal portion, a middle portion, and a radially distal portion. The radially proximal portion has a first cambered cross-section, the middle portion has a second uncambered cross-section, and the radially distal portion has a third cambered cross-section. The first cambered cross-section is cambered in an opposite sense to the third cambered cross-section.
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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：US20160083075A1
公开(公告)日：2016-03-24
申请号：US14854380
申请日：2015-09-15
Applicant: ROLLS-ROYCE PLC
Inventor： Matthew MOXON
CPC classification number: B64C11/008 , B64C3/385 , B64C3/52 , B64C11/46 , B64C29/0033 , B64D45/00 , B64D2045/0085 , Y02T50/14
Abstract: An aircraft (40). The aircraft comprises a plurality of propellers (46) mounted to wings (44). Each propeller comprises at least one blade (72, 74) coupled to a respective propeller cyclic actuator (78) configured to cyclically alter the pitch of the respective blade (72, 74) as the propeller rotates. The aircraft (40) is configured such that provision of cyclic pitch to the propeller (46) twists at least a portion of the wing (44) about a span of the wing (46) relative to the fuselage (42), to thereby adjust the local angle of incidence of the wing (46).
Abstract translation: 飞机（40）。 飞行器包括安装到机翼（44）上的多个螺旋桨（46）。 每个螺旋桨包括联接到相应的螺旋桨循环致动器（78）的至少一个叶片（72,74），所述螺旋桨循环致动器构造成在推进器旋转时周期性地改变相应叶片（72,74）的桨距。 飞行器（40）构造成使得向螺旋桨（46）提供循环桨距绕机翼（46）相对于机身（42）的跨度扭转翼（44）的至少一部分，从而调整 机翼的局部入射角（46）。
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Patent Agency Ranking
公开(公告)号：US20190300160A1
公开(公告)日：2019-10-03
申请号：US16294271
申请日：2019-03-06
Applicant: ROLLS-ROYCE plc
Inventor： Matthew MOXON
Abstract: A strut for an aeroplane wing includes a first part adapted to be connected at one end portion to a fuselage of the aeroplane; a second part connected at a first end portion to a second end portion of the first part and adapted to be connected at a second end portion to either a wing, a pylon or a nacelle of the aeroplane, the second part being angled to the first part to define an inverted gull-strut arrangement. Either the first part or the second part includes a compartment to house a landing gear in a folded configuration
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公开(公告)号：US20180073382A1
公开(公告)日：2018-03-15
申请号：US15692619
申请日：2017-08-31
Applicant: ROLLS-ROYCE PLC
Inventor： Matthew MOXON
CPC classification number: F01D11/24 , F01D17/145 , F04D27/001 , F04D27/002 , F04D27/0246 , F05D2220/323 , F05D2240/307 , F05D2260/82 , F05D2270/11 , F05D2270/30
Abstract: A method of controlling a rotor tip clearance in a gas turbine engine (10). The method comprises determining an engine or component remaining useful life Tr, and controlling a tip clearance control arrangement (38) to maintain a rotor tip clearance (36) at a target tip clearance Dtarget. The target tip clearance Dtarget is determined in accordance with a function of remaining engine life Tr.
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公开(公告)号：US20170305524A1
公开(公告)日：2017-10-26
申请号：US15483721
申请日：2017-04-10
Applicant: ROLLS-ROYCE plc
Inventor： Matthew MOXON
Abstract: An aircraft has an internal combustion engine and a wing including a hollow structural member. The aircraft has an electrical network including: at least one alternating current electrical generator configured to be driven by the internal combustion engine; an electrical motor configured to drive an aircraft propulsor; at least one conductor configured to electrically couple the electrical motor and the electrical generator; wherein the electrical conductor is formed of the hollow structural member of the aircraft wing.
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公开(公告)号：US20170121031A1
公开(公告)日：2017-05-04
申请号：US15280170
申请日：2016-09-29
Applicant: ROLLS-ROYCE plc
Inventor： Rory D. STIEGER , Matthew MOXON , Mikko MATTILA
CPC classification number: B64D33/02 , B64C1/0009 , B64C21/06 , B64C2230/04 , B64D27/02 , B64D27/14 , B64D2033/0226 , Y02T50/12 , Y02T50/166
Abstract: An aircraft (10) comprising a fuselage (12), the fuselage (10) comprising at least first and second inwardly tapering portions (20, 22) extending in a generally rearward direction from an aft end of the fuselage (12), each inwardly tapering portion (20, 22) comprising a boundary layer ingesting propulsor (36) mounted thereon.
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公开(公告)号：US20160207630A1
公开(公告)日：2016-07-21
申请号：US14976414
申请日：2015-12-21
Applicant: ROLLS-ROYCE plc
Inventor： Matthew MOXON
CPC classification number: B64D27/10 , B64C39/10 , B64C2039/105 , B64D27/02 , B64D27/14
Abstract: An aircraft (2) comprises at least first and second gas turbine engines (10a, 10b) arranged in a line extending generally normally to an aircraft longitudinal axis (A), each engine (10a, 10b) comprising at least one compressor or turbine rotor disc (32-42) defining a respective rotational plane (D32-D42). The rotational plane (D32-D42) of at least one of the rotors (32-42) of at least one of the engines (10a, 10b) is angled relative to the aircraft longitudinal line (A) such that a burst disc plane of the respective engine (10a, 10b) is nonintersecting with another engine (10a, 10b).
Abstract translation: 飞机（2）包括至少第一和第二燃气涡轮发动机（10a，10b），其布置成大致正常延伸到飞行器纵向轴线（A）的线，每个发动机（10a，10b）包括至少一个压缩机或涡轮转子 （32-42）限定相应的旋转平面（D32-D42）。 至少一个发动机（10a，10b）的至少一个转子（32-42）的旋转平面（D32-D42）相对于飞机纵向线（A）成角度，使得 各发动机（10a，10b）与另一发动机（10a，10b）不相接。
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