An assembly (50) for an aircraft having a propeller (20), including an engine assembly (10) having an engine shaft (14) configured for driving engagement with the propeller (20). The engine assembly (10) includes first and second heat exchangers (42, 46) configured for circulation of at least one of a liquid coolant and a lubricant therethrough. A wheel well (54) is configured for receiving a retracted landing gear (56). A first cooling duct (60) receives the first heat exchanger (42) and has a first outlet (60o) downstream of the first heat exchanger (42), and a second cooling duct (62) receives the second heat exchanger (46) and has a second outlet (62o) downstream of the second heat exchanger (46). The outlets (60o, 62o) are in direct fluid communication with an environment of the aircraft, and laterally spaced from each other. The wheel well (54) is located between the outlets (60o, 62o). A method of cooling an engine assembly (10) is also discussed.
AIRCRAFT WITH WHEEL WELL BETWEEN COOLING DUCT OUTLETS
FLUGZEUG MIT FAHRWERKSKASTEN ZWISCHEN KÜHLKANALAUSGÄNGEN
AÉRONEF COMPORTANT UN BAIE DE TRAIN D'ATTERRISSAGE ENTRE LES SORTIES DES CONDUITS DE REFROIDISSEMENT
2021-09-29
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
Aircraft with wheel well between cooling duct outlets
Europäisches Patentamt | 2020
|AIRCRAFT WITH WHEEL WELL BETWEEN COOLING DUCT OUTLETS
Europäisches Patentamt | 2019
|AIRCRAFT WITH WHEEL WELL BETWEEN COOLING DUCT OUTLETS
Europäisches Patentamt | 2019
|Improved Trench Film Cooling With Shaped Trench Outlets
Online Contents | 2013
|Improved Trench Film Cooling With Shaped Trench Outlets
Online Contents | 2013
|