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1.
公开(公告)号:US20200173369A1
公开(公告)日:2020-06-04
申请号:US16679562
申请日:2019-11-11
Applicant: ROLLS-ROYCE plc
Inventor: Stephen M. HUSBAND , Ahmed M Y. RAZAK , Paul R. MILLER
Abstract: A method of controlling at least part of a start-up or re-light process of a gas turbine engine, the method comprising: determining when a flame in a combustion chamber of a gas turbine engine is extinguished, during a start-up process or re-light process or during operation; purging the combustion chamber by controlling rotation of a low pressure compressor using a first electrical machine, and controlling rotation of a high pressure compressor using a second electrical machine, the combustion chamber downstream of the low pressure compressor and high pressure compressor; and controlling rotation of the low pressure compressor using the first electrical machine, and controlling rotation of the high pressure compressor using the second electrical machine to restart the start-up process or perform the re-light process.
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2.
公开(公告)号:US20190264615A1
公开(公告)日:2019-08-29
申请号:US16269814
申请日:2019-02-07
Applicant: ROLLS-ROYCE plc
Inventor: Stephen M. HUSBAND , Ahmed MY RAZAK
Abstract: A method of controlling at least a part of a start-up or re-light process of a gas turbine engine, the method comprising: controlling rotation of a low pressure compressor using a first electrical machine to increase angular velocity of the low pressure compressor; and controlling rotation of a high pressure compressor using a second electrical machine to restrict angular velocity of the high pressure compressor while the angular velocity of the low pressure compressor is increased.
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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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5.
公开(公告)号:US20200173368A1
公开(公告)日:2020-06-04
申请号:US16679576
申请日:2019-11-11
Applicant: ROLLS-ROYCE plc
Inventor: Stephen M. HUSBAND , Ahmed M Y RAZAK , Paul R. MILLER
Abstract: A method of controlling at least part of a start-up or re-light process of a gas turbine engine, the method comprising: controlling ignition within a combustion chamber of the gas turbine engine; controlling rotation of a low pressure compressor using a first electrical machine, and controlling rotation of a high pressure compressor using a second electrical machine, the combustion chamber downstream of the low pressure compressor and high pressure compressor; determining if an exit pressure of the high pressure compressor is equal to or greater than a self-sustaining threshold pressure; and in response to determining that the exit pressure of the high pressure compressor is equal to or greater than the self-sustaining threshold pressure, ceasing controlling rotation of the low pressure compressor using the first electrical machine, and/or the high pressure compressor using a second electrical machine.
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公开(公告)号:US20190312428A1
公开(公告)日:2019-10-10
申请号:US16299765
申请日:2019-03-12
Applicant: ROLLS-ROYCE plc
Inventor: Chloe J. PALMER , Stephen M. HUSBAND
Abstract: A superconducting fault current limiter (10) is shown. It comprises a cryostatic cooling system (20) for containing a cooling medium (26), a superconducting wire (30) immersed in the cooling medium (26) and configured to carry a current, the superconducting wire (30) becoming non-superconducting above a critical current density, and a plurality of heat dissipation elements spaced along and projecting from the superconducting wire (30), wherein the heat dissipation elements have an electrically insulating coating, and whereby the heat dissipation elements transfer heat from the superconducting wire (30) into the cooling medium (26).
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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:US20220131435A1
公开(公告)日:2022-04-28
申请号:US17572242
申请日:2022-01-10
Applicant: ROLLS-ROYCE plc
Inventor: Stephen M. HUSBAND , Jeffrey HOBDAY
Abstract: Fault-tolerant electric drive systems including a machine having a rotor and a stator having coils arranged in pairs. Each coil in each pair separated by 180 degrees, a first phase (ϕA) having one of the coil pairs and a phase drive circuit connected therewith, a second phase (ϕB) having a second one of the coil pairs and a second phase drive circuit connected therewith, a third phase (ϕC) having a third one of the coil pairs and a third phase drive circuit connected therewith, and a fourth phase having a fourth one of the coil pairs and a fourth phase drive circuit connected therewith. Further included is a controller connected with the first, second, third and fourth phase drive circuits to control operation thereof.
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公开(公告)号:US20210075285A1
公开(公告)日:2021-03-11
申请号:US17007436
申请日:2020-08-31
Applicant: ROLLS-ROYCE plc
Inventor: Stephen M. HUSBAND , Jeffrey HOBDAY
IPC: H02K3/28 , H02K1/16 , H02K3/14 , H02K3/24 , H02K3/42 , H02K3/493 , H02K7/18 , H02K9/19 , H02K21/14 , B64D27/10 , B64D27/24 , F02C7/266
Abstract: Fault-tolerant four-phase electric drive systems are provided. One such system comprises: a rotary electric machine having a permanent magnet rotor and an alternate-wound stator having eight evenly-spaced coils arranged in pairs, each coil in each pair being separated by 180 degrees; a first phase (ΦA) comprising a first one of the coil pairs and a first phase drive circuit connected therewith; a second phase (ΦB) separated by +45 degrees from the first phase and comprising a second one of the coil pairs and a second phase drive circuit connected therewith; a third phase (ΦC) separated by +90 degrees from the first phase and comprising a third one of the coil pairs and a third phase drive circuit connected therewith; a fourth phase (ΦD) separated by +135 degrees from the first phase and comprising a fourth one of the coil pairs and a fourth phase drive circuit connected therewith; and a controller connected with the first, second, third and fourth phase drive circuits to control operation thereof.
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