Abstract: The example embodiments are directed to a heat dissipation system for an electric aircraft engine. In an example, the aircraft engine includes an electric system configured to power an engine fan to provide thrust to an aircraft, the electric system including cooling channels to receive a coolant to cool one or more components of the electric system, a power source to power the electric system, and one or more guide vanes connected to the cooling channels of the electric system and configured to receive the coolant heated by and output from the cooling channels, wherein the one or more guide vanes are further to cool the heated coolant and transfer the cooled coolant back to the cooling channels of the electric system. By dissipating heat from electric system via the guide vanes, the cooling system can provide sufficient cooling without adding additional drag to the aircraft.

Abstract: The example embodiments are directed to a heat dissipation system for an electric aircraft engine. In an example, the aircraft engine includes an electric system configured to power an engine fan to provide thrust to an aircraft, the electric system including cooling channels to receive a coolant to cool one or more components of the electric system, a power source to power the electric system, and one or more guide vanes connected to the cooling channels of the electric system and configured to receive the coolant heated by and output from the cooling channels, wherein the one or more guide vanes are further to cool the heated coolant and transfer the cooled coolant back to the cooling channels of the electric system. By dissipating heat from electric system via the guide vanes, the cooling system can provide sufficient cooling without adding additional drag to the aircraft.