Gas turbine engine

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.