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US 2019/0193865 A1Published application
Nacelle for an aircraft turbojet engine with hybrid air inlet and fan cowl
AssigneeSafran Nacelles
InventorPatrick BOILEAU
Life of this patent
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Abstract
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.
Claims9
A nacelle for an aircraft turbojet engine, the nacelle comprising:
- an air inlet comprising a leading edge of the nacelle extending downstream by an inner wall and an outer wall of the air inlet;
- and
- a fan cowl, defining in a closed position an aerodynamic continuity with the outer wall of the nacelle, the fan cowl surrounding a fan casing of the aircraft turbojet engine, wherein the air inlet defines at least one portion of the fan cowl.
Dependencies are inferred from the claim text.