公开(公告)号：US11976611B2

公开(公告)日：2024-05-07

申请号：US17940421

申请日：2022-09-08

申请人： ROLLS-ROYCE plc

发明人： Paul R Davies ,  Gareth E Moore ,  Stephen M Husband ,  David R Trainer ,  David P Scothern ,  Luke George

IPC分类号： F02K3/06 ,  F01D15/10

CPC分类号： F02K3/06 ,  F01D15/10 ,  F05D2220/323 ,  F05D2220/36

摘要： 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.

公开(公告)号：US11905887B2

公开(公告)日：2024-02-20

申请号：US17988504

申请日：2022-11-16

申请人： ROLLS-ROYCE plc

发明人： Gareth E Moore ,  Paul R Davies ,  Stephen M Husband ,  David R Trainer ,  David P Scothern ,  Luke George ,  Douglas M M Herbert

IPC分类号： F02C7/262 ,  F01D15/10

CPC分类号： F02C7/262 ,  F01D15/10 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2260/85 ,  F05D2270/092 ,  F05D2270/093

摘要： 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.

公开(公告)号：US11873109B2

公开(公告)日：2024-01-16

申请号：US18053015

申请日：2022-11-07

申请人： ROLLS-ROYCE plc

发明人： David R. Trainer ,  Francisco Javier Chivite Zabalza ,  Mark Sweet ,  Luke George ,  Gian Incerpi

IPC分类号： B64D27/24 ,  H02J1/10 ,  H02J7/34 ,  H02M3/28

CPC分类号： B64D27/24 ,  H02J1/106 ,  H02J7/34 ,  H02M3/28 ,  B64D2221/00 ,  H02J2310/44

摘要： The disclosure relates to an electrical power system for providing a stabilised DC voltage to a power bus. Example embodiments include an electrical power system comprising: a DC power bus having first and second DC power bus terminals; an electrical storage unit having first and second terminals, the second terminal connected to the second DC power bus terminal; a DC:DC converter having first and second DC:AC converters and a transformer connected between the first and second DC:AC converters, the first DC:AC converter connected between the first terminal of the electrical storage unit and the first DC power bus terminal; and a controller connected to control a switching operation of one or both of the first and second DC:AC converters.

公开(公告)号：US20220021059A1

公开(公告)日：2022-01-20

申请号：US17305634

申请日：2021-07-12

申请人： ROLLS-ROYCE plc

发明人： Luke George ,  Douglas Campbell ,  Robert Martin ,  Andrew Limmack

IPC分类号： H01M50/231 ,  H01M50/24 ,  H01M50/227 ,  H01M50/249

摘要： A battery case for housing a battery and a method of fabricating such a battery case are provided. The battery case may be a battery case for an aircraft. The battery case comprises an enclosure having a cavity for housing the battery. An internal surface of the enclosure facing the cavity includes a protective lining comprising cork and a phenolic binder.

公开(公告)号：US11879413B2

公开(公告)日：2024-01-23

申请号：US17940480

申请日：2022-09-08

申请人： ROLLS-ROYCE plc

发明人： Paul R Davies ,  Gareth E Moore ,  Stephen M Husband ,  David R Trainer ,  David P Scothern ,  Luke George

IPC分类号： F02K3/06 ,  F01D15/10 ,  F02C7/141

CPC分类号： F02K3/06 ,  F01D15/10 ,  F02C7/141 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/213 ,  F05D2260/606

摘要： 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.

公开(公告)号：US11837894B2

公开(公告)日：2023-12-05

申请号：US17957778

申请日：2022-09-30

申请人： Rolls-Royce plc

发明人： David R Trainer ,  Francisco Javier Chivite Zabalza ,  Mark Sweet ,  Gian Incerpi ,  Luke George

IPC分类号： H02J7/00 ,  H02M3/335 ,  B64D27/24

CPC分类号： H02J7/0031 ,  B64D27/24 ,  H02M3/33573 ,  B64D2221/00 ,  H02J2207/20

摘要： 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.