An aircraft includes a fuel cell system including a fuel cell powered by hydrogen received from a supply of hydrogen, and a propulsion unit including a conduit through which a flow of air is propelled. A first heat exchanger transfers heat from the fuel cell to a coolant fluid located in a coolant loop, and a second heat exchanger is located in the conduit for heating the air passing through the conduit by transferring heat to the air from the coolant fluid via the second heat exchanger. This configuration serves to cool the fuel cell while increasing the efficiency of the propulsion unit.
AIRCRAFT PROPULSION SYSTEM WITH INTEGRATED FUEL CELL COOLING
2024-07-04
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
AIRCRAFT PROPULSION SYSTEM WITH INTEGRATED FUEL CELL COOLING
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