US 12,092,030 B2
Gas turbine engine
Natalie C Wong, Bristol (GB); Jonathan A Cherry, Bristol (GB); Paul R Davies, Bristol (GB); David A Jones, Bristol (GB); Andrew J Newman, Bristol (GB); Benjamin J Sellers, Bath (GB); and Stephen J Bradbrook, Clevedon (GB)
Assigned to ROLLS-ROYCE PLC, London (GB)
Filed by ROLLS-ROYCE plc, London (GB)
Filed on Sep. 8, 2022, as Appl. No. 17/940,055.
Prior Publication US 2023/0167768 A1, Jun. 1, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 7/12 (2006.01); F02C 6/20 (2006.01); F02C 7/32 (2006.01)
CPC F02C 7/12 (2013.01) [F02C 6/20 (2013.01); F02C 7/32 (2013.01); F05D 2220/323 (2013.01); F05D 2220/76 (2013.01); F05D 2260/213 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A gas turbine engine for an aircraft, the gas turbine engine comprising, in axial flow sequence, a heat exchanger module, and a core engine, the core engine comprising, in axial flow sequence, an intermediate-pressure compressor, a high-pressure compressor, a high pressure turbine, and a low-pressure turbine, the high-pressure compressor being rotationally connected to the high-pressure turbine by a first shaft, the intermediate-pressure compressor being rotationally connected to the low-pressure turbine by a second shaft, the heat exchanger module being in fluid communication with the core engine by an inlet duct, the heat exchanger module comprising a central hub and a plurality of heat transfer elements extending radially outwardly from the central hub and spaced in a circumferential array, for transfer of heat energy from a first fluid contained within the heat transfer elements to an inlet airflow passing over a surface of the heat transfer elements prior to entry of the airflow into an inlet to the core engine, and wherein
the gas turbine engine further comprises a first electric machine and a second electric machine, the first electric machine is rotationally connected to the first shaft, the first electric machine is positioned downstream of the heat exchanger module relative to a direction of the airflow, and the second electrical machine is rotationally connected to the second shaft,
the first electric machine is coaxial with the first shaft, and the entire first electric machine is positioned upstream of the intermediate-pressure compressor.