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公开(公告)号：US20210083605A1
公开(公告)日：2021-03-18
申请号：US16570616
申请日：2019-09-13
Applicant: Rolls-Royce Corporation
Inventor： David Russell Trawick
IPC: H02P6/10
Abstract: A system for control of a torque developed by an electric machine, based on a rotary position of a rotary component. The rotation of the rotary component is dependent on a rotation of a rotary shaft of the electric machine. The system utilizes a rotary position sensor to detect specific positions of the rotary component and allows altering the torque of the electric machine based on the specific rotary positions. The system allows altering the torque when a specific gear tooth of a downstream or upstream gear is in a contact position with another meshing component. The electric machine may be configured to operate as an electric motor driving a gearbox or an electric generator driven by a gearbox.
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公开(公告)号：US20240246684A1
公开(公告)日：2024-07-25
申请号：US18159455
申请日：2023-01-25
Applicant: Rolls-Royce Corporation
Inventor： David Russell Trawick
IPC: B64D27/10 , B64C11/30 , B64D27/24 , B64D35/00 , B64D41/00 , F02C7/36 , H02J7/00 , H02K7/102 , H02K7/116 , H02K7/18 , H02K11/00
CPC classification number: B64D27/10 , B64C11/30 , B64D27/24 , B64D35/00 , B64D41/00 , F02C7/36 , H02J7/0013 , H02K7/102 , H02K7/116 , H02K7/1823 , H02K11/0094 , B64D2027/026 , B64D2221/00
Abstract: An example aircraft includes a parallel propulsion unit, the parallel propulsion unit comprising: a propulsor configured to provide forward propulsion of the aircraft; a gas turbine engine configured to drive the propulsor; an electrical machine configured to generate, for output via one or more electrical busses, electrical energy using mechanical energy derived from the gas turbine engine; and a power sharing module configured to control a ratio of the mechanical energy derived from the gas turbine engine used to drive the propulsor and used to generate electrical energy; and a plurality of series propulsion units, each series propulsion unit comprising a respective propulsor of a plurality of propulsors that are configured to provide forward propulsion of the aircraft and a respective electrical machine each configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from one or more electrical busses.
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公开(公告)号：US11840148B2
公开(公告)日：2023-12-12
申请号：US17651161
申请日：2022-02-15
Applicant: Rolls-Royce Corporation , Rolls-Royce Electrical Norway AS , Rolls-Royce Singapore Pte. Ltd.
Inventor： David Loder , David Russell Trawick , Eirik Mathias Husum , Erlend Engevik , Roar Furuhaug , Chandana Jayampathi Gajanayake
CPC classification number: B60L3/003 , B60L3/04 , B64D27/24 , B60L2200/10 , B60L2210/30 , B64D2027/026
Abstract: A system includes a first generator configured to output a first plurality of AC signals; a second generator configured to output a second plurality of AC signals; a first set of rectifiers configured to convert the first plurality of AC signals into a first plurality of DC signals for output onto a first DC bus, wherein each of the first set of rectifiers includes a respective contactor configured to de-couple a DC output of the respective rectifier from the first DC electrical bus; and a second set of rectifiers configured to convert the second plurality of AC signals into a second plurality of DC signals for output onto a second DC bus, wherein each of the second set of rectifiers includes a respective contactor configured to de-couple a DC output of the respective rectifier from the second DC bus.
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公开(公告)号：US11808311B2
公开(公告)日：2023-11-07
申请号：US17207068
申请日：2021-03-19
Applicant: Rolls-Royce Corporation
Inventor： Mathew Hill , David Russell Trawick
CPC classification number: F16D3/50 , F16D1/10 , F16D2001/103 , Y10S464/90 , Y10T403/472 , Y10T403/475 , Y10T403/7033
Abstract: An electrically insulated shaft coupling may include a first metallic portion, a second metallic portion, and an electrically insulating portion that separates the first metallic portion and the second metallic portion. The first metallic portion may include a first plurality of splines configured to interface with splines of a first rotating shaft, and the second metallic portion comprises a second plurality of splines configured to interface with splines of a second rotating shaft.
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公开(公告)号：US20230257127A1
公开(公告)日：2023-08-17
申请号：US17651177
申请日：2022-02-15
Applicant: Rolls-Royce Corporation , Rolls-Royce Electrical Norway AS , Rolls-Royce Singapore Pte. Ltd.
Inventor： David Loder , David Russell Trawick , Eirik Mathias Husum , Erlend Engevik , Roar Furuhaug , Chandana Jayampathi Gajanayake
CPC classification number: B64D27/24 , B60L3/003 , B60L2200/10 , B64D2027/026
Abstract: A system for providing propulsive electrical power for an aircraft, the system comprising: a first generator configured to output a first plurality of AC electrical signals; a second generator configured to output a second plurality of AC electrical signals; a first set of rectifiers configured to convert the first plurality of AC electrical signals into a first plurality of DC electrical signals for output onto a first DC electrical bus of a plurality of DC electrical busses; and a second set of rectifiers configured to convert the second plurality of AC electrical signals into a second plurality of DC electrical signals for output onto a second DC electrical bus of the plurality of DC electrical busses, wherein each rectifier of the plurality of rectifiers includes a respective controller of a plurality of controllers, and wherein the plurality of controllers are configured to coordinate response to detected faults.
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Patent Agency Ranking
公开(公告)号：US20240380295A1
公开(公告)日：2024-11-14
申请号：US18314453
申请日：2023-05-09
Applicant: Rolls-Royce Corporation
Inventor： David Russell Trawick , Mathew Gregory Hill
IPC: H02K21/16 , H02K1/2789 , H02K7/12 , H02K7/18 , H02K7/20
Abstract: An example electrical machine is described that includes active segments for variable voltage generation. The electrical machine includes a drive shaft, a fixed rotor segment, an active rotor segment, and an actuator mechanism. The fixed rotor segment is coupled to the drive shaft, where the fixed rotor segment has affixed thereon first permanent magnets of alternating polarity. The active rotor segment axially is adjacent to the fixed rotor segment along the drive shaft. The active rotor segment also has affixed thereon second permanent magnets of alternating polarity. The actuator mechanism is configured to articulate the active rotor segment relative to the fixed rotor segment and thereby alter a phase of the second permanent magnets relative to the first permanent magnets in order to change a first voltage generated by the electrical machine to a second voltage generated by the electrical machine.
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公开(公告)号：US20230261595A1
公开(公告)日：2023-08-17
申请号：US17651156
申请日：2022-02-15
Applicant: Rolls-Royce Corporation , Rolls-Royce Electrical Norway AS , Rolls-Royce Singapore Pte. Ltd.
Inventor： David Loder , David Russell Trawick , Eirik Mathias Husum , Erlend Engevik , Roar Furuhaug , Chandana Jayampathi Gajanayake
CPC classification number: H02P9/006 , B64D27/10 , B64D27/24 , B64D2027/026
Abstract: A turbo-generator system for generating propulsive electrical power for an aircraft includes an electric machine comprising: a rotor configured to be rotated by a gas-turbine of the turbo-generator system; a stator comprising: a first active section comprising first windings surrounding a first portion of the rotor; and a second active section comprising second windings surrounding a second portion of the rotor.
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公开(公告)号：US20210229821A1
公开(公告)日：2021-07-29
申请号：US16774606
申请日：2020-01-28
Applicant: Rolls-Royce Corporation
Abstract: An example system includes a first plurality of nacelles located on a first side of an aircraft, wherein each nacelle of the first plurality of nacelles includes an electric motor coupled to a propulsor, wherein an outboard nacelle of the first plurality of nacelles includes an electrical energy storage system (ESS) coupled to a first electrical bus; and a second plurality of nacelles located on a second side of the aircraft, wherein each nacelle of the second plurality of nacelles includes an electric motor coupled to a propulsor, wherein an outboard nacelle of the second plurality of nacelles includes an ESS coupled to a second electrical bus.
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公开(公告)号：US12095405B2
公开(公告)日：2024-09-17
申请号：US17651156
申请日：2022-02-15
Applicant: Rolls-Royce Corporation , Rolls-Royce Electrical Norway AS , Rolls-Royce Singapore Pte. Ltd.
Inventor： David Loder , David Russell Trawick , Eirik Mathias Husum , Erlend Engevik , Roar Furuhaug , Chandana Jayampathi Gajanayake
IPC: H02P9/00 , B64D27/10 , B64D27/24 , B64D27/02 , H02P101/25 , H02P101/30
CPC classification number: H02P9/006 , B64D27/10 , B64D27/24 , B64D27/026 , B64D2221/00 , H02P2101/25 , H02P2101/30
Abstract: A turbo-generator system for generating propulsive electrical power for an aircraft includes an electric machine comprising: a rotor configured to be rotated by a gas-turbine of the turbo-generator system; a stator comprising: a first active section comprising first windings surrounding a first portion of the rotor, and a second active section comprising second windings surrounding a second portion of the rotor.
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公开(公告)号：US20240246690A1
公开(公告)日：2024-07-25
申请号：US18159506
申请日：2023-01-25
Applicant: Rolls-Royce Corporation
Inventor： David Russell Trawick
IPC: B64D27/10 , B64C11/30 , B64D27/24 , B64D35/00 , B64D41/00 , F02C6/00 , F02C7/36 , H02K7/102 , H02K7/116 , H02K7/18 , H02K11/00
CPC classification number: B64D27/10 , B64C11/30 , B64D27/24 , B64D35/00 , B64D41/00 , F02C6/00 , F02C7/36 , H02K7/102 , H02K7/116 , H02K7/1823 , H02K11/0094 , B64D2027/026
Abstract: An example aircraft includes a parallel propulsion unit, the parallel propulsion unit comprising: a propulsor configured to provide forward propulsion of the aircraft; a gas turbine engine configured to drive the propulsor; an electrical machine configured to generate, for output via one or more electrical busses, electrical energy using mechanical energy derived from the gas turbine engine; and a power sharing module configured to control a ratio of the mechanical energy used to drive the propulsor and used to generate electrical energy; and a plurality of series propulsion units, each series propulsion unit comprising a respective propulsor of a plurality of propulsors that are configured to provide vertical propulsion of the aircraft and a respective electrical machine of a plurality of electrical machines, each respective electrical machine configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from one or more electrical busses.
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