-
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.
-
Patent Agency Ranking
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.
-
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.
-
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.
-
公开(公告)号：US20230184163A1
公开(公告)日：2023-06-15
申请号：US17940748
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: F02C6/20 , F02C7/32 , F02C7/36 , F05D2220/323 , F05D2220/70
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 shaft power PSHAFT (W); and a ratio R of:
R
=
(
Maximum
Electrical
Power
Generated
=
P
E
M
1
)
(
Maximum
Shaft
Power
=
P
S
H
A
F
T
)
is in a range of between 0.005 and 0.020.-
公开(公告)号：US20230167786A1
公开(公告)日：2023-06-01
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 , F05D2220/36 , F05D2220/323 , 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.
-
-
-
-
-
Search Results
6
records
(took 0.03 seconds)
