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公开(公告)号：US20240077021A1
公开(公告)日：2024-03-07
申请号：US18233531
申请日：2023-08-14
Applicant: ROLLS-ROYCE plc
Inventor： Paul R DAVIES , Richard G MOCHRIE , David A JONES
CPC classification number: F02C7/16 , B64D27/10 , F05D2260/20
Abstract: A thermal management system for an aircraft includes a first gas turbine engine, one or more first electric machines rotatably coupled to the first gas turbine engine, a first thermal bus, and a first heat exchanger. Waste heat energy generated by at least one first gas turbine engine, and first electric machine, transfers to the first heat transfer fluid. The first heat exchanger directs a first proportion of the first heat transfer fluid through a first heat dissipation portion wherein a first proportion of the waste heat energy transfers to a first dissipation medium dependent on the first dissipation medium temperature and mass flow rate. The first heat exchanger directs a second proportion of the first heat transfer fluid through a second heat dissipation portion wherein the second proportion of waste heat energy transfers to a second dissipation medium dependent on the second dissipation medium temperature and mass flow rate.
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公开(公告)号：US20230167785A1
公开(公告)日：2023-06-01
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 , F05D2220/36 , F05D2220/323
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=PEM1)/(Maximum Dry Thrust=T)
is in a range of between 2.0 and 10.0.-
公开(公告)号：US20240077025A1
公开(公告)日：2024-03-07
申请号：US18233619
申请日：2023-08-14
Applicant: ROLLS-ROYCE PLC
Inventor： Paul R DAVIES , David A JONES , Alexander T JOYCE , Richard G MOCHRIE
CPC classification number: F02C7/16 , F02C6/18 , F05D2220/323 , F05D2260/213
Abstract: 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 is exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a dissipation medium.
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4.发明公开公开(公告)号：US20230182918A1
公开(公告)日：2023-06-15
申请号：US17988538
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 , F01D15/10 , B64D27/10 , B64D2027/026
Abstract: Aircraft power and propulsion systems and methods of operating the systems, one method includes: operating electric machines of gas turbine engines as generators to extract mechanical power from spools and generating electrical power therefrom; meeting an electrical power demand of a plurality of electrical loads connected with an electrical system by supplying the plurality of electrical loads with electrical power generated by the electric machines; determining when there is an electrical system and/or the gas turbine engine fault and an amount of electrical power generated by the power and propulsion system is reduced to a lower level; and responsive to the determination: during a time period ΔT, controlling the plurality of electrical loads reducing the electrical power demand; and during the time period ΔT, meeting at least part of the electrical power demand of the plurality of electrical loads by discharging the electrical energy storage system.
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公开(公告)号：US20240084735A1
公开(公告)日：2024-03-14
申请号：US18233510
申请日：2023-08-14
Applicant: ROLLS-ROYCE plc
Inventor： Paul R DAVIES , David A JONES
CPC classification number: F02C7/14 , B64D27/10 , F02C7/18 , F05D2220/323 , F05D2260/213
Abstract: A thermal management system for an aircraft includes a first gas turbine engine, one or more first electric machines, first thermal bus and heat exchanger. The first thermal bus includes a first heat transfer fluid in a closed loop flow sequence, between the first gas turbine engine, or each first electric machine, and the first heat exchanger. Waste heat energy transfers to the first heat transfer fluid. The first heat exchanger configures to transfer waste heat energy from the first heat transfer fluid to a dissipation medium. During steady-state operation of the first gas turbine engine, the first heat transfer fluid entering the first heat exchanger has a temperature of TFLUID(° C.), and a temperature of an inlet air flow entering the first gas turbine engine has a temperature TAIR(° C.) and a ratio B is in a range of between 5.0-18.0.
B
=
(
First
Heat
Transfer
Fluid
Temperature
=
T
FLUID
)
(
Inlet
Air
Temperature
=
T
AIR
)-
Patent Agency Ranking
公开(公告)号：US20210079850A1
公开(公告)日：2021-03-18
申请号：US16914827
申请日：2020-06-29
Applicant: ROLLS-ROYCE plc
Inventor： Paul R DAVIES
Abstract: An aircraft gas turbine engine (10) comprises a main engine shaft (22, 23), a main engine shaft bearing arrangement (36, 49, 50) configured to rotatably support the main engine shaft (22, 23), and an electric machine (30) comprising a rotor (32) and a stator (34). The rotor (32) is mounted to the main engine shaft (22, 23) and is rotatably supported by a further electric machine bearing arrangement (70, 72) extending between the rotor (34) and the stator (32), and the stator (32) is mounted to static structure (38) of the gas turbine engine (10).
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公开(公告)号：US20240076052A1
公开(公告)日：2024-03-07
申请号：US18233495
申请日：2023-08-14
Applicant: ROLLS-ROYCE plc
Inventor： Paul R DAVIES , David A JONES , Richard G MOCHRIE
CPC classification number: B64D33/08 , F02C7/12 , F05D2220/323 , F05D2260/213
Abstract: A thermal management system for an aircraft includes a first gas turbine engine, one or more first electric machines, a first thermal bus, and a first heat exchanger. The first thermal bus includes a first heat transfer fluid in a closed loop flow sequence, between the first gas turbine engine, the or each first electric machine, and the first heat exchanger. Waste heat energy generated by at least one of the first gas turbine engine, and the or each first electric machine, is transferred to first heat transfer fluid. When airspeed of aircraft is less than Mn0.6, the first heat exchanger transfers the waste heat energy from the first heat transfer fluid to a first dissipation medium. When the airspeed of the aircraft is greater than Mn0.6, the first heat exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a second dissipation medium.
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公开(公告)号：US20230219694A1
公开(公告)日：2023-07-13
申请号：US17940030
申请日：2022-09-08
Applicant: ROLLS-ROYCE plc
Inventor： Benjamin J SELLERS , Andrew J NEWMAN , Gordon MARGARY , Paul R DAVIES , Stephen J BRADBROOK
IPC: B64D33/08
CPC classification number: B64D33/08 , B64D2027/026
Abstract: 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：US20230182920A1
公开(公告)日：2023-06-15
申请号：US17988341
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: B64D35/02 , B64D27/10 , B64D27/24 , B64D31/06 , B64D2027/026
Abstract: A twin-engine aircraft power and propulsion system including first and second propulsive gas turbine engines, each having combustion equipment and a first and second spool; first, second, third, and fourth electrical power generation sub-systems including electric machines respectively mechanically coupled with the first spool of the first propulsive gas turbine engine, the second spool of the first propulsive gas turbine engine, the first spool of the second propulsive gas turbine engine, and the second spool of the second propulsive gas turbine engine; and first, second, third, and fourth power channels respectively connected with distribution sides of the first electric machine, second electric machine, third electric machine, and fourth electric machine.
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公开(公告)号：US20230167769A1
公开(公告)日：2023-06-01
申请号：US17940473
申请日：2022-09-08
Applicant: ROLLS-ROYCE PLC
Inventor： Andrew J NEWMAN , Martin N GOODHAND , Paul R DAVIES , David A JONES , Stephen J BRADBROOK
CPC classification number: F02C7/14 , F02C7/18 , F05D2220/323 , F05D2260/213 , F05D2260/232
Abstract: A cooling system for an aircraft comprises an apparatus, a heat exchanger, and a vapour cycle machine. The apparatus comprises a first fluid being circulated to provide cooling to the apparatus, with the heat exchanger being configured to transfer waste heat energy from the first fluid to a second fluid. The second fluid has a temperature T2 (°C), and the vapour cycle machine is configured to increase a temperature T1 (°C) of the first fluid, to a temperature greater than T2 (°C).
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