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公开(公告)号：US20200023983A1
公开(公告)日：2020-01-23
申请号：US16458321
申请日：2019-07-01
Applicant: ROLLS-ROYCE plc
Inventor： Matthew MOXON
IPC: B64D27/24
Abstract: A modular energy storage system within a vehicle, wherein the energy storage system comprises a plurality of discrete energy storage units which are movable within the vehicle and selectively securable in a variety of positions.
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公开(公告)号：US20190128570A1
公开(公告)日：2019-05-02
申请号：US16142362
申请日：2018-09-26
Applicant: ROLLS-ROYCE plc
Inventor： Matthew MOXON
IPC: F25B11/04 , B64D13/06 , B64D27/24 , B64D27/02 , F02C7/14 , H01M10/613 , H01M10/625 , H01M10/663 , H01M10/6567 , H01M10/6556 , H01M8/04029 , H02K9/19 , H02K11/00
Abstract: A thermal management system comprises a first heat exchanger configured to exchange heat between a first component and a first working fluid, a first working fluid compressor downstream in first working fluid flow of the first heat exchanger and configured to compress the first working fluid, a second heat exchanger downstream in first working fluid flow of the compressor and configured to exchange heat between the first working fluid and a second working fluid and an expander downstream in first working fluid flow of the second heat exchanger, and configured to expand and cool first working fluid and deliver cooled first working fluid to the first heat exchanger. The system further comprises a third heat exchanger upstream in second working fluid flow of the second heat exchanger, and configured to exchange heat between a second component and the second working fluid.
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公开(公告)号：US20180057179A1
公开(公告)日：2018-03-01
申请号：US15793529
申请日：2017-10-25
Applicant: ROLLS-ROYCE plc
Inventor： Matthew MOXON
CPC classification number: B64D27/10 , B64C39/10 , B64C2039/105 , B64D27/02 , B64D27/14
Abstract: An aircraft comprises at least first and second gas turbine engines arranged in a line extending generally normally to an aircraft longitudinal axis (A), each engine comprising at least one compressor or turbine rotor disc defining a respective rotational plane (D32-D42). The rotational plane (D32-D42) of at least one of the rotors of at least one of the engines is angled relative to the aircraft longitudinal line (A) such that a burst disc plane of the respective engine is nonintersecting with another engine.
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公开(公告)号：US20180038245A1
公开(公告)日：2018-02-08
申请号：US15649800
申请日：2017-07-14
Applicant: ROLLS-ROYCE PLC
Inventor： Matthew MOXON
IPC: F01K25/04
CPC classification number: F01K25/04 , F01K7/00 , F01K25/00 , F01K25/103 , F02C1/10 , F02C1/105 , F02C6/18 , F02C9/00 , F02C9/24 , F05D2270/804 , G01N21/532 , G01N2021/0314 , G01N2021/8416
Abstract: A turbomachinery control system for controlling supercritical working fluid turbomachinery. The control system includes a light emitter to project light through working fluid of the turbomachinery toward a primary light detector provided within a line of sight to the emitter. The system further includes one or more secondary light detectors spaced from the line of sight, and a controller determining one or both of an intensity of light detected by the primary detector relative to the detected light intensity by the secondary detector, and wavelength of light detected by the primary detector relative to wavelength of light detected by the secondary detector. The controller determines the working fluid proximity of the critical point based on one or both of the determined relative intensity and determined relative wavelength, and controlling an actuator to control turbomachinery inlet or outlet conditions in accordance with the working fluid determined proximity of the critical point.
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公开(公告)号：US20150144742A1
公开(公告)日：2015-05-28
申请号：US14537112
申请日：2014-11-10
Applicant: ROLLS-ROYCE PLC
Inventor： Matthew MOXON
CPC classification number: B64C23/005 , B64C3/00 , B64C3/28 , B64C9/18 , B64C11/00 , B64C39/00 , B64D27/10 , B64D27/12 , B64D27/24 , Y02T50/44 , Y02T50/64
Abstract: An aircraft (40). The aircraft (40) comprises a propulsion system comprising a pair of internal combustion engines (10) each driving an electrical power generator (56), each electrical power generator (56) being electrically coupled to a plurality of electrically driven propulsors (46). The propulsors (46) are located forward of a leading edge (45) of the wings (44) such that an airstream generated by the propulsors flows over the wings (44) in use. Each internal combustion engine (10) and electrical generator (56) is mounted on a respective wing (44) outboard of a centre of thrust (70) of the propulsors (46) on that wing (44).
Abstract translation: 飞机（40）。 飞机（40）包括推进系统，其包括一对驱动发电机（56）的内燃机（10），每个发电机（56）电耦合到多个电驱动推进器（46）。 推进器（46）位于翼（44）的前缘（45）的前方，使得由推进器产生的气流在使用中在翼（44）上流动。 每个内燃机（10）和发电机（56）安装在该翼（44）上的推进器（46）的推力中心（70）外侧的相应翼（44）上。
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Patent Agency Ranking
公开(公告)号：US20240327022A1
公开(公告)日：2024-10-03
申请号：US18602098
申请日：2024-03-12
Applicant: ROLLS-ROYCE plc
Inventor： Matthew MOXON
CPC classification number: B64D37/30 , B64D27/12 , B64D37/04 , F17C7/02 , F17C2201/0128 , F17C2201/0133 , F17C2205/0134 , F17C2221/012 , F17C2221/033 , F17C2223/0161 , F17C2265/066 , F17C2270/0189
Abstract: A hydrogen fuelled aircraft includes a fuselage, a wing, at least one hydrogen fuelled gas turbine engine, at least one hydrogen fuel tank configured to store liquid or supercritical hydrogen and a hydrogen fuel line configured to delivery hydrogen fuel from the fuel tank to the engine. The gas turbine engine and the hydrogen fuel tank are each installed externally on the wing, and the hydrogen fuel line does not pass through the fuselage.
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公开(公告)号：US20210387715A1
公开(公告)日：2021-12-16
申请号：US17344248
申请日：2021-06-10
Applicant: ROLLS-ROYCE plc
Inventor： Matthew MOXON
Abstract: An aircraft comprising a wing having a spanwise lift distribution extending from a root to a tip, the lift distribution defining an inboard region defining a positive lift contribution, an outboard region defining a negative lift contribution, and an intermediate region defining a neutral lift contribution, the neutral region being spaced from the tip and from the root. A propulsion system is provided, comprising a wing mounted propulsor. The wing mounted propulsor has a rotational axis (x) positioned substantially at a span of the wing where a value of δLift/δSpan is at a maximum for the span of the wing, and may be located at the intermediate region along the span of the wing.
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公开(公告)号：US20200005657A1
公开(公告)日：2020-01-02
申请号：US16429156
申请日：2019-06-03
Applicant: ROLLS-ROYCE plc
Inventor： Matthew MOXON
Abstract: An aerodrome system for an aerodrome is provided. The aerodrome system comprises a plurality of light emitting elements configured to emit light from a surface of the aerodrome upon which aircraft may take-off, land and manoeuvre; and a controller operatively coupled to each of the light emitting elements so as to selectively control the light emitting elements, wherein the light emitting elements form pixels of a display and the controller is configured to control an image displayed by the display so as to display and demarcate at least one runway for aircraft to take-off or land, wherein the light emitting elements are spaced such that the controller may display the runway with a variable orientation and the controller is further configured to change the image displayed by the display so as to change the orientation of the runway.
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公开(公告)号：US20160355272A1
公开(公告)日：2016-12-08
申请号：US15133728
申请日：2016-04-20
Applicant: ROLLS-ROYCE plc
Inventor： Matthew MOXON
CPC classification number: B64D35/04 , B64D27/02 , B64D2027/026 , Y02T50/44
Abstract: An aircraft propulsion system includes at least first and second propulsor arrangements. Each propulsor arrangement includes an internal combustion engine configured to mechanically drive a plurality of propulsors. At least one of the propulsors of each propulsor arrangement is driveable via a shaft and at least one reduction gearbox. Each internal combustion engine is coupled to a motor generator arrangement configured to drive at least one of the mechanically driven propulsors when in a motor mode, and to generate electrical power when in a generating mode. The system further includes an electrical interconnector configured to transfer electrical power between the first and second propulsor arrangements.
Abstract translation: 飞行器推进系统至少包括第一和第二推进装置。 每个推进装置包括配置成机械地驱动多个推进器的内燃机。 每个推进器装置的推进器中的至少一个可经由轴和至少一个减速齿轮箱驱动。 每个内燃机耦合到电动发电机装置，其被配置为当处于电动机模式时驱动机械驱动的推进器中的至少一个，并且在处于发电模式时产生电力。 该系统还包括电互连器，其配置成在第一和第二推进装置之间转移电力。
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公开(公告)号：US20160332741A1
公开(公告)日：2016-11-17
申请号：US15135040
申请日：2016-04-21
Applicant: ROLLS-ROYCE plc
Inventor： Matthew MOXON
CPC classification number: B64D33/02 , B64C3/50 , B64C11/001 , B64C15/00 , B64C21/00 , B64D27/02 , B64D27/10 , B64D27/24 , B64D29/04 , B64D33/04 , B64D2027/026 , B64D2033/0226 , Y02T50/166 , Y02T50/44
Abstract: An aircraft including trailing edge flaps, a wing mounted propulsor positioned such that the flaps are located in a slipstream of the first propulsor in use when deployed. The aircraft further including a thrust vectorable propulsor configured to selectively vary the exhaust efflux vector of the propulsor in at least one plane. The thrust vectorable propulsor includes a ducted fan configurable between a first mode, in which the fan provides net forward thrust to the aircraft, and a second mode in which the fan provides net drag to the aircraft. The fan is positioned to ingest a boundary layer airflow in use when operating in the first mode.
Abstract translation: 一种包括后缘翼片的飞行器，安装在机翼上的推进器，其被定位成使得当展开时，翼片位于第一推进器的滑流中。 所述飞机还包括推力可矢量的推进器，其构造成在至少一个平面中选择性地改变推进器的排气流出矢量。 可推力可推动推进器包括可在第一模式之间配置的管道风扇，其中风扇向飞机提供净前推力，以及第二模式，其中风扇向飞机提供净拖动。 当在第一模式下操作时，风扇被定位成摄取使用中的边界层气流。
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