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公开(公告)号：US11976611B2
公开(公告)日：2024-05-07
申请号：US17940421
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: F02K3/06 , F01D15/10 , F05D2220/323 , F05D2220/36
Abstract: A gas turbine engine for an aircraft comprises, in axial flow sequence, a compressor module, a combustor module, and a turbine module, with a first electric machine being rotationally connected to the turbine module. The first electrical machine is configured to generate a maximum electrical power PEM1 (W), and the gas turbine engine is configured to generate a maximum dry thrust T (N); and a ratio S of:
S
=
(
Maximum
Electrical
Power
Generated
=
P
E
M
1
)
(
Maximum
Dry
Thrust
=
T
)
is in a range of between 2.0 and 10.0.-
Patent Agency Ranking
公开(公告)号：US12046894B2
公开(公告)日：2024-07-23
申请号：US17956924
申请日：2022-09-30
Applicant: ROLLS-ROYCE plc
Inventor： David R Trainer , Mark Sweet
Abstract: There is provided a current limiting diode 200 comprising a gate 206, a source 202, a drain 204 electrically connected to the source by an n-channel or p-channel 220 and a thermoelectric generator 208; wherein the source and the gate are electrically connected by a fill structure 210, and wherein the thermoelectric generator is configured to: generate a thermoelectric voltage by absorbing heat from the n-channel or p-channel and rejecting heat to a heat sink in a current limiting condition; and apply the thermoelectric voltage between the gate and the source.
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公开(公告)号：US11879413B2
公开(公告)日：2024-01-23
申请号：US17940480
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: F02K3/06 , F01D15/10 , F02C7/141 , F05D2220/323 , F05D2220/36 , F05D2260/213 , F05D2260/606
Abstract: An aircraft gas turbine engine includes a heat exchanger module, and a core engine. The core engine includes an intermediate-pressure compressor, high-pressure compressor, and high and low-pressure turbines. The high-pressure compressor rotationally connects to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor rotationally connects to the low-pressure turbine by a second shaft. The heat exchanger module fluidly communicates with the core engine by an inlet duct. The heat exchanger module includes a central hub and multiple heat transfer elements extending radially from the hub and spaced in a circumferential array, for heat energy transfer from a first fluid within the elements to an inlet airflow passing over a surface of the elements prior to airflow entry into an inlet to the core engine. The gas turbine engine further includes a first electric machine rotationally connected to the first shaft, and positioned downstream of the heat exchanger module.
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公开(公告)号：US11837894B2
公开(公告)日：2023-12-05
申请号：US17957778
申请日：2022-09-30
Applicant: Rolls-Royce plc
Inventor： David R Trainer , Francisco Javier Chivite Zabalza , Mark Sweet , Gian Incerpi , Luke George
CPC classification number: H02J7/0031 , B64D27/24 , H02M3/33573 , B64D2221/00 , H02J2207/20
Abstract: An electrical power system including: an electrical power source, a power electronics converter, an electrical network, a current limiting diode and a controllable circuit interruption device, wherein: the current limiting diode is configured to limit a fault current passing between the electrical power source and the electrical network in a fault condition; and the controllable circuit interruption device is configured to interrupt the fault current in response to a determination that the electrical power system is in the fault condition.
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公开(公告)号：US11905887B2
公开(公告)日：2024-02-20
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
CPC classification number: F02C7/262 , F01D15/10 , 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：US11121639B2
公开(公告)日：2021-09-14
申请号：US16747760
申请日：2020-01-21
Applicant: ROLLS-ROYCE plc
Inventor： David R Trainer , Zhigang Sun , Ellis F H Chong
Abstract: Disclosed herein is a converter for converting an AC voltage to a DC voltage, the converter comprising: a first H-bridge circuit comprising a first AC terminal for receiving an AC voltage, a second AC terminal, a first DC terminal and a second DC terminal; a second H-bridge circuit comprising a first AC terminal for receiving an AC voltage, a second AC terminal, a first DC terminal and a second DC terminal; an isolation block arranged between the second AC terminal of the first H-bridge circuit and the second AC terminal of the second H-bridge circuit; and a DC voltage output of the converter with a first terminal and a second terminal; wherein: the first terminal of the DC voltage output is connected to the first DC terminal of the first H-bridge circuit and the first DC terminal of the second H-bridge circuit; and the second terminal of the DC voltage output is connected to the second DC terminal of the first H-bridge circuit and the second DC terminal of the second H-bridge circuit.
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