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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：US20230184197A1
公开(公告)日：2023-06-15
申请号：US17940531
申请日：2022-09-08
Applicant: ROLLS-ROYCE PLC
Inventor： Benjamin J. SELLERS , Andrew J NEWMAN , David A JONES , Stephen J BRADBROOK
CPC classification number: F02K3/06 , B64D27/20 , F02K3/068 , F05D2200/14 , F05D2220/323
Abstract: An gas turbine engine for an aircraft includes, in axial flow sequence, a compressor module, a combustor module, and a turbine module, together with a first electrical machine rotationally connected to the turbine module. The combustor module has a combustor volume V (cm3). In use, at a full power condition, the gas turbine engine has a maximum corrected core flow Q (m3/sec), and a ratio T of:
T
=
(
Maximum
Corrected
Core
Flow
=
Q
)
(
Combustor
volume
=
V
)
is in a range of between 450 and 2,500.-
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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