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公开(公告)号：US11982230B2
公开(公告)日：2024-05-14
申请号：US18233619
申请日：2023-08-14
申请人： ROLLS-ROYCE PLC
CPC分类号： F02C7/16 , F25B27/02 , F02C6/18 , F05D2220/323 , F05D2260/213
摘要： A thermal management system for an aircraft comprises a first gas turbine engine, a first thermal bus, a first heat exchanger, and a chiller. The first thermal bus comprises a first heat transfer fluid, with the first heat transfer fluid being in fluid communication, in a closed loop flow sequence, between the first gas turbine engine, the first heat exchanger, and the chiller. Waste heat energy generated by the first gas turbine engine, is transferred to the first heat transfer fluid. The chiller is configured to lower a temperature of the first heat transfer fluid prior to the first heat transfer fluid being circulated through the gas turbine engine. The first heat exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a dissipation medium.
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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
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
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.
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公开(公告)号：US12092030B2
公开(公告)日：2024-09-17
申请号：US17940055
申请日：2022-09-08
申请人： ROLLS-ROYCE plc
发明人： Natalie C Wong , Jonathan A Cherry , Paul R Davies , David A Jones , Andrew J Newman , Benjamin J Sellers , Stephen J Bradbrook
CPC分类号： F02C7/12 , F02C6/20 , F02C7/32 , F05D2220/323 , F05D2220/76 , F05D2260/213
摘要： An aircraft gas turbine engine includes a heat exchanger module, and a core engine including an intermediate-pressure compressor, a high-pressure compressor, a high pressure turbine, and a low-pressure turbine. The high-pressure compressor is connected to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor is connected to the low-pressure turbine by a second shaft. The heat exchanger module includes a central hub and heat transfer elements extending radially from the central hub and spaced in a circumferential array, for transferring heat energy from a fluid within the heat transfer elements to an inlet airflow passing over the heat transfer elements prior to entry of the airflow into an inlet to the core engine. The gas turbine engine further includes a first electric machine connected to the first shaft and positioned downstream of the heat exchanger module, and a second electric machines connected to the second shaft.
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公开(公告)号：US11952945B2
公开(公告)日：2024-04-09
申请号：US18233518
申请日：2023-08-14
申请人： ROLLS-ROYCE plc
发明人： Paul R Davies , Alexander T Joyce , David A Jones
CPC分类号： F02C7/16 , F02C6/18 , F25B27/02 , F05D2220/323 , F05D2260/213
摘要： A thermal management system for an aircraft includes a first gas turbine engine, first thermal bus, first heat exchanger, one or more first ancillary systems, vapour compression system, one or more second ancillary systems and second heat exchanger. A waste heat energy generated by a first gas turbine engine, and a first ancillary system, transfers to the first heat transfer fluid. A waste heat energy generated by a second ancillary system transfers to a second heat transfer fluid, and the second heat exchanger transfers the waste heat energy from the second heat transfer fluid to the first heat transfer fluid. The waste heat energy generated by a second ancillary system transfers to the first heat transfer fluid, and the first heat exchanger transfers the waste heat energy to a dissipation medium. The waste heat energy transferred to the second heat transfer fluid ranges from 20 kW to 300 kW.
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公开(公告)号：US12092037B2
公开(公告)日：2024-09-17
申请号：US17940419
申请日：2022-09-08
申请人： ROLLS-ROYCE PLC
CPC分类号： F02C7/32 , F02C6/00 , F02C6/20 , F02C7/12 , F05D2220/323 , F05D2220/76 , F05D2260/213
摘要： A gas turbine engine for an aircraft includes, 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 total electrical power PEM1 (W), and the gas turbine engine is configured to generate a total shaft power PSHAFT (W); and a ratio R of:
R
=
(
Total
Shaft
Power
=
P
SHAFT
)
(
Total
Electrical
Power
Generated
=
P
EM
1
)
is in a range of between 0.005 and 0.020.-
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
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：US11384655B2
公开(公告)日：2022-07-12
申请号：US16914867
申请日：2020-06-29
申请人： ROLLS-ROYCE plc
发明人： Paul R Davies
摘要： An aircraft gas turbine engine (10) comprises a main engine shaft (22, 23), a main engine shaft bearing arrangement (36, 44, 49, 50) configured to rotatably support the main engine shaft (22, 23) and an electric machine (30) comprising a rotor (34) and a stator (32). The rotor (34) is mounted to the main engine shaft (22, 23) and is rotatably supported by the main engine shaft bearing arrangement (36, 44, 49, 50), and the stator (32) is mounted to static structure (46) of the gas turbine engine (10).
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公开(公告)号：US12006055B2
公开(公告)日：2024-06-11
申请号：US17940030
申请日：2022-09-08
申请人： ROLLS-ROYCE plc
CPC分类号： B64D33/08 , B64D27/026
摘要： A cooling system for an aircraft comprises a gas turbine engine, an ancillary apparatus, and a heat exchanger. The gas turbine engine 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 an electrical power PEM1 (W). The heat exchanger is configured to transfer a total waste heat energy Q (W) generated by the gas turbine engine and the ancillary apparatus, to an airflow passing through the heat exchanger, and a ratio S of:
S
=
(
Total
Electrical
Power
Generated
=
P
EM
1
)
(
Total
Heat
Energy
Rejected
to
Airflow
=
Q
)
is in a range of between 0.50 and 5.00.-
公开(公告)号：US11994067B2
公开(公告)日：2024-05-28
申请号：US17940055
申请日：2022-09-08
申请人： ROLLS-ROYCE plc
发明人： Natalie C Wong , Jonathan A Cherry , Paul R Davies , David A Jones , Andrew J Newman , Benjamin J Sellers , Stephen J Bradbrook
CPC分类号： F02C7/12 , F02C6/20 , F02C7/32 , F05D2220/323 , F05D2220/76 , F05D2260/213
摘要： An aircraft gas turbine engine includes a heat exchanger module, and a core engine including an intermediate-pressure compressor, a high-pressure compressor, a high pressure turbine, and a low-pressure turbine. The high-pressure compressor is connected to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor is connected to the low-pressure turbine by a second shaft. The heat exchanger module includes a central hub and heat transfer elements extending radially from the central hub and spaced in a circumferential array, for transferring heat energy from a fluid within the heat transfer elements to an inlet airflow passing over the heat transfer elements prior to entry of the airflow into an inlet to the core engine. The gas turbine engine further includes a first electric machine connected to the first shaft and positioned downstream of the heat exchanger module, and a second electric machines connected to the second shaft.
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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
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
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.
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