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：US20250052196A1

公开(公告)日：2025-02-13

申请号：US18795312

申请日：2024-08-06

Applicant: ROLLS-ROYCE plc

Inventor： Andrew J. NEWMAN ,  Michael YEANDEL

IPC: F02C7/141 ,  B64D27/10 ,  B64D27/40

Abstract: The present disclosure relates to an airframe assembly comprising an airframe support structure defining an engine void and configured to support a gas turbine engine along an engine axis of the engine void; a thermal enclosure configured to surround the gas turbine within the engine void; a heat exchange channel formed between an outer flow-bounding wall of the engine void and an inner wall defined by the thermal enclosure, configured to convey a cooling flow through the engine void outside of the thermal enclosure for the gas turbine engine; and a heat exchanger mounted to the airframe support structure for heat exchange between the cooling flow and a working fluid provided to the heat exchanger.

公开(公告)号：US20230167768A1

公开(公告)日：2023-06-01

申请号：US17940055

申请日：2022-09-08

Applicant: ROLLS-ROYCE plc

Inventor： Natalie C. WONG ,  Jonathan A. CHERRY ,  Paul R. DAVIES ,  David A. JONES ,  Andrew J. NEWMAN ,  Benjamin J. SELLERS ,  Stephen J. BRADBROOK

IPC: F02C7/12 ,  F02C6/20 ,  F02C7/32

CPC classification number: F02C7/12 ,  F02C6/20 ,  F02C7/32 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2260/213

Abstract: An aircraft gas turbine engine includes a heat exchanger module, and a core engine including an intermediate-pressure compressor, a high-pressure compressor, a high pressure turbine, and a low-pressure turbine. The high-pressure compressor is connected to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor is connected to the low-pressure turbine by a second shaft. The heat exchanger module includes a central hub and heat transfer elements extending radially from the central hub and spaced in a circumferential array, for transferring heat energy from a fluid within the heat transfer elements to an inlet airflow passing over the heat transfer elements prior to entry of the airflow into an inlet to the core engine. The gas turbine engine further includes a first electric machine connected to the first shaft and positioned downstream of the heat exchanger module, and a second electric machines connected to the second shaft.