公开(公告)号：US20230167775A1

公开(公告)日：2023-06-01

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

IPC: F02C7/32 ,  F02C6/00 ,  F02C6/20 ,  F02C7/12

CPC classification number: F02C7/32 ,  F02C6/00 ,  F02C6/20 ,  F02C7/12 ,  F05D2220/76 ,  F05D2220/323 ,  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

S
H
A
F
T










Total Electrical Power Generated = P


E
M
1










is in a range of between 0.005 and 0.020.

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

IPC: F02C6/20 ,  F02C7/32 ,  F02C7/36

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

IPC: F02K3/06 ,  F01D15/10 ,  F02C7/141

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.