The present disclosure relates to a nacelle for an aircraft turbojet engine that includes an air inlet having a leading edge of the nacelle extending forward by an inner wall and an outer wall of the air inlet and a fan cowling defining, in a closed position, aerodynamic continuity with the outer wall of the nacelle, intended for surrounding a turbojet engine fan cowling. The air inlet is designed to define at least one portion of the fan cowling. The present disclosure also relates to a propulsion assembly that includes a nacelle surrounding a turbojet engine.
NACELLE FOR AN AIRCRAFT TURBOJET ENGINE WITH HYBRID AIR INLET AND FAN COWL
2019-06-27
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
Nacelle for an aircraft turbojet engine with hybrid air inlet and fan cowl
Europäisches Patentamt | 2020
|Turbojet engine nacelle with translatable upstream cowl
Europäisches Patentamt | 2015
|