Thermal management air duct for airborne fuel cell systems

Abstract

The present invention relates to an aircraft comprising a cooling system integrated into the fuselage, and at least one propeller driven by an electric motor adapted to propel the aircraft, the cooling system comprising: at least one cooling duct (or air duct), installed inside the fuselage of the aircraft, provided with an air inlet and an air outlet, the cooling duct being designed to allow air to flow between the air inlet and the air outlet; at least one heat exchanger positioned inside the cooling duct, the heat exchanger being designed to transfer thermal energy to the air flowing in the cooling duct; wherein the air inlet is positioned in an area of overpressure generated by the air accelerated by the rotation of the propeller, and the air outlet is strategically positioned on an outer surface of the fuselage passed over by the air flow accelerated by the rotation of the propeller, generating an area of lower pressure facilitating the flow of air through the cooling duct, thereby allowing efficient dissipation of heat through the heat exchanger.

Dependencies are inferred from the claim text.