A cooling system for an engine of an aircraft of a having hybrid-electric propulsion system including a nacelle body including a bottom cooling air intake disposed below a propeller hub for supplying air to an oil-air cooler, wherein the bottom cooling air intake includes a splitter dividing the bottom cooling air intake into a first channel and a second channel.
COOLING SYSTEM CONFIGURATIONS FOR AN AIRCRAFT HAVING HYBRID-ELECTRIC PROPULSION SYSTEM
KÜHLSYSTEMKONFIGURATIONEN FÜR EIN FLUGZEUG MIT EINEM HYBRID-ELEKTRISCHEN ANTRIEBSSYSTEM
CONFIGURATIONS DE SYSTÈME DE REFROIDISSEMENT POUR UN AÉRONEF AYANT UN SYSTÈME DE PROPULSION HYBRIDE-ÉLECTRIQUE
30.11.2022
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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