Patent ID: 11879413
Assignee: ROLLS-ROYCE PLC
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. A gas turbine engine for an aircraft, the gas turbine engine comprising:
a 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, and
the intermediate-pressure compressor being rotationally connected to the low-pressure turbine by a second shaft;

a 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, and configured to transfer 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, the heat exchanger module being in fluid communication with the core engine by an inlet duct; and

a first electric machine rotationally connected to the first shaft and positioned downstream of the heat exchanger module, the first electric machine having:
a maximum electrical power output of between 180 kW and 500 kW,
an axial length in the range of between 0.20m and 0.45m, and
a maximum diameter in the range of between 0.15m and 0.39m

wherein the first electric machine is positioned axially upstream of the core engine and configured to rotate about a rotational axis of the core engine.