Nacelle for turbojet engine, comprising openings of front cowls for access to fixing points of the nacelle
AssigneeSafran Nacelles
InventorsPatrick Boileau, Pierre Caruel
Life of this patent
Estimating the term…
Abstract
A nacelle for a bypass turbojet engine includes a cascade thrust reverser provided with reversal cascades arranged around an annular stream of fresh air, beneath front cowls. The cascades move backward with movable rear cowls, opening side passages in the annular stream, which receive the cascades for directing the fresh air flow forward, the bypass turbojet engine. The bypass turbojet engine includes fixing points, and the nacelle includes outer hatches closing openings of the front cowls, which are arranged radially outside the fixing points for access thereto, each hatch opening including a contour with edges of two front cowls.
Claims5
A nacelle for a bypass turbojet engine, the nacelle comprising:
- front cowls and a cascade thrust reverser equipped with thrust reverser cascades and movable rear cowls, the thrust reverser cascades being disposed around an annular flow path of fresh air, under the front cowls, and the thrust reverser cascades moving back with the movable rear cowls opening lateral passages in the annular flow path of fresh air, wherein the lateral passages receive the thrust reverser cascades to direct a fresh air flow forward,
- the bypass turbojet engine including fastening points,
- the front cowls comprising openings disposed radially outside the fastening points to access the fastening points, and
- the nacelle comprising external hatches closing the openings of the front cowls,
- wherein each of the openings includes a contour delimited by edges of two of the front cowls, and
- wherein the thrust reverser cascades are radially disposed outside the fastening points when the cascade thrust reverser is closed.
Dependencies are inferred from the claim text.