A fuel tank inerting system of an aircraft includes a first air flow (Al) provided from a first source having a first temperature and a second air flow (Ac) including cabin outflow air having a second temperature. The first temperature is greater than the second temperature. A fuel tank inerting heat exchanger (34) is arranged in fluid communication with both the first air flow and the second air flow. At least one air separating module (30) is configured to separate an inert gas from the first air flow output from the fuel tank inerting heat exchanger.
AIRCRAFT
LUFTFAHRZEUG
AÉRONEF
2023-05-03
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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