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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：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：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.
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