Reverse flow gas turbine engine having electric machine

An aircraft engine assembly comprising:

• a gas turbine engine having a high pressure compressor, a high pressure turbine, a high pressure shaft coupling the high pressure compressor with the high pressure turbine, a low pressure turbine, and a low pressure shaft coupled to the low pressure turbine, the high pressure turbine located forward of the high pressure compressor, and the low pressure turbine located on a forward end of the gas turbine engine;
• a propeller located on a forward end of the gas turbine engine and coupled via the low pressure shaft with the low pressure turbine;
• an intake channel of the gas turbine engine configured to receive an incoming flow of air and form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction;
• and
• an electric machine coupled with the low pressure shaft and located on a side of the high pressure compressor opposite of the high pressure turbine and proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated,
• wherein the high pressure compressor includes a flow path, the flow path defined between an inner flow surface and an outer flow surface, the flow path structured to convey the incoming flow of air to the compressor, and further including an anti-ice flow passage from the intake channel directing a flow of anti-ice air to the high pressure compressor.