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公开(公告)号：US20190123626A1
公开(公告)日：2019-04-25
申请号：US16132524
申请日：2018-09-17
Applicant: ROLLS-ROYCE plc , Rolls-Royce Marine AS
Inventor： Giles E. HARVEY , Astrid ROKKE
CPC classification number: H02K21/28 , F01D15/10 , F05D2220/32 , F05D2260/00 , F05D2260/20 , H02K1/32 , H02K7/003 , H02K7/08 , H02K7/088 , H02K7/1823 , H02K9/19 , H02K16/005
Abstract: An electric motor generator system has a hollow rotatable shaft, a coil spar, and a plurality of magnet portions. The hollow rotatable shaft has a central longitudinal axis. The coil spar comprises one or more coil assemblies and is positioned concentrically within the hollow rotatable shaft. Each of the magnet portions is shaped to conform to a radially inwardly facing surface of the shaft. Each of the plurality of magnet portions abuts conformally against the radially inwardly facing surface of the shaft between the radially inwardly facing surface and the or each coil assembly.
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公开(公告)号：US20210179286A1
公开(公告)日：2021-06-17
申请号：US16952147
申请日：2020-11-19
Applicant: ROLLS-ROYCE plc , Rolls-Royce Deutschland Ltd & Co KG
Inventor： Giles E. HARVEY , Gideon Daniel VENTER
Abstract: An aircraft hybrid propulsion system comprises an internal combustion engine, an electric motor a propulsor and a combining gearbox. The internal combustion engine is coupled to a first input of the combining gearbox, the electric motor is coupled to a second input of the combining gearbox, and the propulsor is coupled to an output of the combining gearbox, such that the propulsor is driveable in use by either or both of the internal combustion engine and the electric motor. Each of the internal combustion engine and the electric motor is coupled to its respective input by a respective clutch.
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公开(公告)号：US20210164392A1
公开(公告)日：2021-06-03
申请号：US17032477
申请日：2020-09-25
Applicant: ROLLS-ROYCE plc
Inventor： Giles E. HARVEY
Abstract: A gas turbine engine, and arrangements of turbine blades around an exhaust nozzle of an engine core. Example embodiments include a gas turbine engine for an aircraft comprising: an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, the engine core comprising an inlet upstream of the compressor and an exhaust nozzle at a downstream outlet of the turbine; a fan located upstream of the engine core inlet; and a set of exhaust nozzle vanes spanning the exhaust nozzle, the turbine comprising a first row of turbine blades upstream of the exhaust nozzle vanes and a second row of turbine blades downstream of the exhaust nozzle guide vanes, one or more of the exhaust nozzle guide vanes comprising a passage configured to direct airflow downstream from the first row of turbine blades towards the second row of turbine blades.
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公开(公告)号：US20200070990A1
公开(公告)日：2020-03-05
申请号：US16546372
申请日：2019-08-21
Applicant: ROLLS-ROYCE plc
Inventor： Giles E. HARVEY
Abstract: An aircraft propulsion system comprises first and second co-axial propulsors, one of the first and second propulsor being positioned forward of the other propulsor. A first electric motor is configured to drive the first propulsor, and a second electric motor is configured to drive the second propulsor. The first electric motor comprising a rotor radially inwardly of the stator, and the second electric motor comprises a rotor radially outwardly of the stator. The stator of the first electric motor is mounted to the stator of the second electric motor.
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Patent Agency Ranking
公开(公告)号：US20200070988A1
公开(公告)日：2020-03-05
申请号：US16546368
申请日：2019-08-21
Applicant: ROLLS-ROYCE plc
Inventor： Giles E. HARVEY
Abstract: An aircraft propulsion system comprises first and second propulsors. An epicyclic reduction gearbox is coupled to an input shaft. The reduction gearbox comprises a sun gear coupled to the input shaft, a plurality of planet gears which mesh with the sun gear and are mounted to a planet carrier, and a ring gear which meshes with the plurality of planet gears. The first propulsor is located upstream of the second propulsor The first propulsor is coupled to the sun gear, and the second propulsor is coupled to one of the planet carrier and the ring gear.
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公开(公告)号：US20170058779A1
公开(公告)日：2017-03-02
申请号：US15139839
申请日：2016-04-27
Applicant: ROLLS-ROYCE plc
Inventor： Giles E. HARVEY , Martyn RICHARDS
CPC classification number: F02C7/224 , F01D25/20 , F02C7/12 , F02C7/16 , F05D2220/32 , F05D2240/50 , F05D2260/205 , F05D2260/4031 , F05D2260/40311 , F05D2260/98 , F23R3/34 , F23R3/42 , Y02T50/675
Abstract: A thermal management system for a gas turbine engine comprises a plurality of first heat generating sub-systems arranged in operable communication with the engine, a fuel supply sub-system, a fuel circulation sub-system, and one or more combustors. The fuel supply sub-system is adapted to supply a de-oxygenated fuel to the fuel circulation sub-system, and the fuel circulation sub-system is adapted to circulate the de-oxygenated fuel to lubricate and cool each of the plurality of first heat generating sub-systems, and then to combust the de-oxygenated fuel in the or each combustor.
Abstract translation: 燃气涡轮发动机的热管理系统包括布置成与发动机可操作地连通的多个第一发热子系统，燃料供应子系统，燃料循环子系统和一个或多个燃烧器。 燃料供应子系统适于向燃料循环子系统供应脱氧燃料，并且燃料循环子系统适于使脱氧燃料循环以润滑和冷却多个第一热量 产生子系统，然后燃烧该或每个燃烧器中的脱氧燃料。
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公开(公告)号：US20200227966A1
公开(公告)日：2020-07-16
申请号：US16720463
申请日：2019-12-19
Applicant: ROLLS-ROYCE plc
Inventor： Giles E. HARVEY , Paul A. SMEETON , Ellis F H CHONG
Abstract: A vehicle propulsion system comprises a first propulsor and a second propulsor. The first and second propulsors are coupled to an electric machine comprising a stator and first and second rotors. Each of the first and second rotors are electromagnetically coupled to the stator. The first rotor is coupled to the first propulsor and the second rotor is coupled to the second propulsor.
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公开(公告)号：US20200070989A1
公开(公告)日：2020-03-05
申请号：US16546362
申请日：2019-08-21
Applicant: ROLLS-ROYCE plc
Inventor： Giles E. HARVEY
IPC: B64D27/24
Abstract: An aircraft propulsion system comprises a vertical lift propulsor mounted within a wing of the aircraft. The vertical propulsor comprises an electric motor comprising a rotor mounted to a plurality of propulsor blades, the motor further comprising a stator. The rotor is provided radially outwardly of the stator.
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公开(公告)号：US20170370284A1
公开(公告)日：2017-12-28
申请号：US15602429
申请日：2017-05-23
Applicant: ROLLS-ROYCE plc
Inventor： Giles E. HARVEY , Glenn A. KNIGHT
CPC classification number: F02C3/04 , F01D9/023 , F02C3/145 , F02C7/143 , F02C7/36 , F02K3/06 , F05D2260/213 , Y02T50/675
Abstract: A gas turbine engine (10) comprises: a low pressure compressor (18) comprising a centrifugal compressor stage (24); a low pressure turbine (44) configured to drive a load (12), the low pressure turbine (44) being provided rearwardly of the low pressure compressor (18); a high pressure turbine (42) provided rearwardly of the low pressure turbine (44); a combustor (40) provided rearwardly of the high pressure turbine (42); a high pressure compressor (32) provided rearwardly of the combustor (40); and an intercooler heat exchanger (28) configured to exchange heat between core airflow (B) exiting the low pressure compressor (18) and fan airflow (A), wherein the high pressure turbine (42) and high pressure compressor (32) are coupled by a high pressure shaft (46), and the low pressure turbine (44), low pressure compressor (18) and load (12) are coupled by a low pressure shaft (22).
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