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.
Un système de refroidissement pour un moteur d'un aéronef comportant un système de propulsion hybride-électrique comprend un corps de nacelle comprenant une admission d'air de refroidissement inférieure disposée au-dessous d'un moyeu d'hélice pour fournir de l'air à un refroidisseur huile-air, l'admission d'air de refroidissement inférieure comprenant un séparateur divisant l'entrée d'air de refroidissement inférieure en un premier canal et un second canal.
COOLING SYSTEM CONFIGURATIONS FOR AN AIRCRAFT HAVING HYBRID-ELECTRIC PROPULSION SYSTEM
CONFIGURATIONS DE SYSTÈME DE REFROIDISSEMENT POUR UN AÉRONEF AYANT UN SYSTÈME DE PROPULSION HYBRIDE-ÉLECTRIQUE
2020-09-10
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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