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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
Applicant: ROLLS-ROYCE PLC
Inventor： Benjamin J Sellers , Andrew J Newman , Gordon Margary , Paul R Davies , Stephen J Bradbrook
CPC classification number: F02C7/32 , F02C6/00 , F02C6/20 , F02C7/12 , F05D2220/323 , F05D2220/76 , F05D2260/213
Abstract: 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：US12006055B2
公开(公告)日：2024-06-11
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
CPC classification number: B64D33/08 , B64D27/026
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.
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