An aircraft fuel system (100;200) can include a fuel line (101;201) configured to transport fuel therein, an exposed aircraft structure (103;203) in direct or indirect thermal communication with the fuel in the fuel line to receive heat from the fuel to provide a deicing or anti-icing heat to the exposed aircraft structure. The exposed aircraft structure can include at least one internal fuel channel (105) in fluid communication with the fuel line for direct thermal communication with the fuel. The system can include a fuel/fluid heat exchanger (207) in fluid communication with the fuel line to transfer heat from the fuel (209) to a fluid to provide indirect thermal communication between the fuel and the exposed aircraft structure.
AIRCRAFT SYSTEMS AND METHODS UTILIZING WASTE HEAT IN FUEL
FLUGZEUGSYSTEME UND VERFAHREN ZUR NUTZUNG VON ABWÄRME IM KRAFTSTOFF
SYSTÈMES ET PROCÉDÉS D'AÉRONEF POUR L'UTILISATION DE LA CHALEUR RÉSIDUELLE DANS LE CARBURANT
2024-07-03
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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