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公开(公告)号：US20230184130A1
公开(公告)日：2023-06-15
申请号：US17988393
申请日：2022-11-16
Applicant: ROLLS-ROYCE plc
Inventor： Gareth E. MOORE , Paul R. DAVIES , Stephen M. HUSBAND , David R. TRAINER , David P. SCOTHERN , Luke GEORGE , Douglas M M HERBERT
Abstract: Aircraft power and propulsion systems, aircraft comprising such power and propulsion systems, and methods of restarting a gas turbine engine of such power and propulsion systems during flight are provided. One such aircraft power and propulsion system comprises: a propulsive gas turbine engine comprising a plurality of spools, combustion equipment, one or more electric machines mechanically coupled with one or more of the spools and an electrically-powered fuel pump for delivering fuel to the combustion equipment; an electrical system connected with the one or more electric machines and the electrically-powered fuel pump, the electrical system comprising an energy storage system; and a control system configured to: responsive to a determination to the effect that a flame in the combustion equipment has been extinguished, control the electrical system to supply electrical power from the energy storage system to the fuel pump during an engine restart attempt.
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公开(公告)号：US20230182917A1
公开(公告)日：2023-06-15
申请号：US17988371
申请日：2022-11-16
Applicant: ROLLS-ROYCE plc
Inventor： Gareth E. MOORE , Paul R. DAVIES , Stephen M. HUSBAND , David R. TRAINER , David P. SCOTHERN , Luke GEORGE , Douglas M. M. HERBERT
CPC classification number: B64D31/06 , B64D27/24 , B64D27/10 , F01D15/10 , F05D2220/76 , F05D2220/323 , B64D2221/00 , B64D2027/026
Abstract: Multi-engine aircraft power and propulsion systems and methods of starting the engines of multi-engine aircraft disclosed, including supplying electrical power from an electrical power source to electric machines of the a first gas turbine engine and operating electric machines as motors to drive rotation of spools of the first gas turbine engine; starting the first gas turbine engine by lighting combustion equipment of the first gas turbine engine; operating the electric machines of the first gas turbine engine as generators to extract mechanical power and generate electrical power from spools of the first gas turbine engine; transferring the electrical power to electric machines of a second gas turbine engine and operating the electric machines as motors to drive rotation of spools of the second gas turbine engine; and starting the second gas turbine engine by lighting combustion equipment of the second gas turbine engine.
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公开(公告)号：US20200025078A1
公开(公告)日：2020-01-23
申请号：US16391592
申请日：2019-04-23
Applicant: ROLLS-ROYCE plc
Inventor： David P. SCOTHERN , Steven P. CULWICK , Shane PERERA , Edward J. SPALTON
Abstract: A gas turbine engine comprising: an engine core comprising a compressor; a compressor bleed valve in communication with the compressor and configured to release bleed air from the compressor; at least one component provided at the inlet of the engine core having a de-icing conduit, configured to receive the bleed air; and a flow controller, configured to provide bleed air to the de-icing conduit of the at least one component in response to either or both of a requirement to de-ice the component and a requirement to release bleed air from the compressor to optimise operation of the core.
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公开(公告)号：US20190284948A1
公开(公告)日：2019-09-19
申请号：US16286714
申请日：2019-02-27
Applicant: ROLLS-ROYCE plc
Inventor： David P. SCOTHERN
Abstract: An electrical power generator system has: an input shaft for receiving a rotary input drive; plural output shafts connected by respective gear shifting arrangements to the input shaft thereby providing different gear ratios between the input shaft and each output shaft; and plural electrical generators powered by rotation of the respective output shafts, electrical power outputs of the generators being combined to supply a total power to a load. The input shaft operates over a range of rotation frequencies, and the gear shifting arrangements are configured to shift the gear ratios between the input shaft and the output shafts such that the output shafts operate over a narrower range of rotation frequencies.
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公开(公告)号：US20190078680A1
公开(公告)日：2019-03-14
申请号：US16059370
申请日：2018-08-09
Applicant: ROLLS-ROYCE plc
Inventor： David A. EDWARDS , David P. SCOTHERN
Abstract: An auxiliary oil supply apparatus for a rotating device (50, 51), the rotating device comprising a primary oil supply (52), a rotating component (50) and a static component (51) situated radially outwardly of a centre of rotation of the rotating component (50) and arranged to collect oil (58) held radially outwardly from the rotating component (50) as the rotating component rotates. The auxiliary oil apparatus comprises a scoop (56) associated with the rotating component (50) and is responsive to a change in a known parameter to move between a first position in the static component (51) to a second position between the static component (51) and the centre of rotation.
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Patent Agency Ranking
公开(公告)号：US20190023406A1
公开(公告)日：2019-01-24
申请号：US16038263
申请日：2018-07-18
Applicant: ROLLS-ROYCE plc
Inventor： David P. SCOTHERN
Abstract: The present disclosure concerns the detection of ice within a system. More specifically, but not exclusively, the disclosure concerns the detection of ice accretion within a gas turbine engine. The apparatus and method relies on heating a first region (38) of a component (44) and comparing the measured temperature of the first region (38) with a second temperature value, possibly measured at a distinct second region (40) of the component (44).
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公开(公告)号：US20170002686A1
公开(公告)日：2017-01-05
申请号：US15171577
申请日：2016-06-02
Applicant: ROLLS-ROYCE plc
Inventor： David P. SCOTHERN
IPC: F01D25/18 , F16J15/447
CPC classification number: F01D25/183 , F01D11/003 , F01D11/04 , F01D11/10 , F02C7/28 , F05D2220/32 , F05D2240/55 , F05D2260/98 , F16J15/40 , F16J15/42
Abstract: A hydraulic seal arrangement including first and second rotatable components, the first defining a first annular trough defined by radially inwardly extending first and second walls, the second component defining a radially outwardly extending web between the walls. The first component includes a second trough defined by the second wall and a third wall axially spaced from the second, the second trough defining an open radially inner end defined by a radially inner end of the second wall such that the first and second annular troughs fluidly communicate around the circumference of the first component via the inner end of the second wall. At a first circumferential position, the second wall of the first component defines a second trough oil inlet providing further fluid communication between the first and second troughs and at a second circumferential position, the third wall of the first component defines a second trough oil outlet.
Abstract translation: 一种液压密封装置，包括第一和第二可旋转部件，第一和第二可转动部件限定由径向向内延伸的第一和第二壁限定的第一环形槽，第二部件在壁之间限定径向向外延伸的纤维网。 第一部件包括由第二壁限定的第二槽和与第二槽轴向隔开的第三壁，第二槽限定由第二壁的径向内端限定的开放的径向内端，使得第一和第二环形槽流体地 通过第二壁的内端在第一部件的周围连通。 在第一圆周位置，第一组件的第二壁限定第二槽式油入口，其在第一和第二槽之间提供进一步的流体连通，并且在第二圆周位置，第一组件的第三壁限定第二槽式油出口。
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公开(公告)号：US20230184171A1
公开(公告)日：2023-06-15
申请号：US17988504
申请日：2022-11-16
Applicant: ROLLS-ROYCE plc
Inventor： Gareth E. MOORE , Paul R. DAVIES , Stephen M. HUSBAND , David R. TRAINER , David P. SCOTHERN , Luke GEORGE , Douglas M M. HERBERT
IPC: F02C7/262
CPC classification number: F02C7/262 , F05D2220/323 , F05D2220/76 , F05D2260/85 , F05D2270/092 , F05D2270/093
Abstract: Multi-engine aircraft power and propulsion systems and methods of restarting an engine of a multi-engine aircraft during fight are provided. One such method comprises: determining a condition to the effect that a flame in the combustion equipment of the second gas turbine engine has been extinguished; responsive to the determination, supplying electrical power from the electrical energy storage system to one or more of the electric machines of the second gas turbine engine and operating said one or more electric machines as motors to limit a reduction in a speed of the one or more spools of the second gas turbine engine following extinguishment of the flame in its combustion equipment; and restarting the second gas turbine engine by relighting the combustion equipment of the second gas turbine engine.
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公开(公告)号：US20230184128A1
公开(公告)日：2023-06-15
申请号：US17940614
申请日：2022-09-08
Applicant: ROLLS-ROYCE plc
Inventor： Paul R. DAVIES , Gareth E. MOORE , Stephen M. HUSBAND , David R. TRAINER , David P. SCOTHERN , Luke GEORGE
CPC classification number: F01D15/10 , F02K3/06 , F05D2220/323 , F05D2260/213 , F05D2260/232 , F05D2260/42 , F05D2200/13 , F05D2200/14
Abstract: A gas turbine engine for an aircraft comprises, in axial flow sequence, a compressor module, a combustor module, and a turbine module. The gas turbine engine further comprises a first electric machine that is rotationally connected to the turbine module, and an electrical energy storage unit. The gas turbine engine is configured to generate a maximum dry thrust T (N). The first electric machine is configured to generate a maximum electrical power PEM1 (W). The electrical energy storage unit has an energy storage capacity E (Wh), a maximum charge rate C (h−1), and a maximum discharge rate D (h−1). The electrical energy storage unit is configured to store electrical energy that may be generated by the first electric machine.
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公开(公告)号：US20200025099A1
公开(公告)日：2020-01-23
申请号：US16376129
申请日：2019-04-05
Applicant: ROLLS-ROYCE plc
Inventor： David P. SCOTHERN
Abstract: A gas turbine engine for an aircraft, comprising: an engine core; a covering configured to cover at least part of the engine core; and an engine accessory that interacts with the engine core or a component of the engine core; wherein the engine accessory is outside the covering.
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