Propulsion system of an aircraft, having an asymmetrical nacelle

Patent metadata

Field	Value
Publication number	US-12377997-B2
Application number	US-202318517316-A
Country	US
Kind code	B2
Filing date	Nov 22, 2023
Priority date	Nov 28, 2022
Publication date	Aug 5, 2025
Grant date	Aug 5, 2025

Abstract

A propulsion system fastened to one side of an aircraft and having a longitudinal axis and a mid-plane and having a nacelle with two inner cowls, two outer cowls, two lower structural elements and two upper structural elements, wherein each outer cowl is articulated on a pylon by hinges with axes parallel to the longitudinal axis. The two outer cowls are contiguous at a separation plane containing the longitudinal axis and making, with the mid-plane, an acute angle. The axes are asymmetrical with respect to the mid-plane.

First claim

The invention claimed is:

1. A propulsion system for an aircraft, said propulsion system having a longitudinal axis and a vertical mid-plane passing through the longitudinal axis, the propulsion system comprising:
a pylon configured to be fastened under a wing with a dihedral angle to a port side of the aircraft,
a turbomachine with a core fastened to the pylon, and
a nacelle in which the turbomachine is housed and which comprises:
two inner cowls arranged around the core,
two outer cowls arranged around the inner cowls, the two outer cowls including a port-side outer cowl and a starboard-side outer cowl demarcated by the vertical mid-plane,
two lower structural elements, each fastening an inner cowl of the two inner cowls to an associated outer cowl of the two outer cowls at a bottom part of the nacelle, and
two upper structural elements, each fastening an inner cowl of the inner cowls to an associated outer cowl of the two outer cowls at a top part of the nacelle,

wherein each outer cowl is articulable and mounted on the pylon via hinges of which axes of the hinges are generally parallel to the longitudinal axis,
wherein, in a closed position and in the top part of the nacelle, the two outer cowls are contiguous at a separation plane that contains the longitudinal axis and makes, with the vertical mid-plane, an acute angle in a clockwise direction in a front view of the propulsion system, and wherein a first axis corresponding to the port-side outer cowl is disposed on a port side with respect to the separation plane, and
wherein a second axis corresponding to the starboard-side outer cowl is disposed on a starboard side with respect to a third axis symmetrical to the first axis corresponding to the port-side outer cowl with respect to the vertical mid-plane.

2. The propulsion system according to claim 1 , wherein, in the bottom part of the nacelle and in the closed position, the two outer cowls and the lower structural elements are contiguous at the separation plane.

3. An aircraft having a wing, wherein at least one propulsion system according to claim 1 is fastened beneath the wing, via the pylon.

4. A propulsion system for an aircraft, said propulsion system having a longitudinal axis and a vertical mid-plane passing through the longitudinal axis, the propulsion system comprising:
a pylon configured to be fastened under a wing with a dihedral angle to a starboard side of the aircraft,
a turbomachine with a core fastened to the pylon, and
a nacelle in which the turbomachine is housed and which comprises:
two inner cowls arranged around the core,
two outer cowls arranged around the inner cowls,
the two outer cowls including a port-side outer cowl and a starboard-side outer cowl demarcated by the vertical mid-plane,
two lower structural elements, each fastening an inner cowl of the two inner cowls to the associated outer cowl of the two outer cowls at a bottom part of the nacelle, and
two upper structural elements, each fastening an inner cowl of the two inner cowls to an associated outer cowl of the two outer cowls at a top part of the nacelle,

wherein each outer cowl is articulable and mounted on the pylon via hinges of which axes of the hinges are generally parallel to the longitudinal axis,
wherein, in a closed position and in the top part of the nacelle, the two outer cowls are contiguous at a separation plane that contains the longitudinal axis and makes, with the vertical mid-plane, an acute angle in a counter-clockwise direction in a front view of the propulsion system, and
wherein a first axis corresponding to the starboard-side outer cowl is disposed on a starboard side with respect to the separation plane, and wherein a second axis corresponding to the port-side outer cowl is disposed on a port side with respect to a third axis symmetrical to the first axis corresponding to the starboard-side outer cowl with respect to the vertical mid-plane.

5. The propulsion system according to claim 4 , wherein, in the bottom part of the nacelle and in the closed position, the two outer cowls and the lower structural elements are contiguous at the separation plane.

6. An aircraft having a wing, wherein at least one propulsion system according to claim 4 is fastened beneath the wing, via the pylon.

Assignees

• Airbus Operations Sas

Inventors

• Gougeon Pascal
• Bellanger Alexandre
• Vanderbauwede Simon

Classifications

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title

• B64D29/02 Primary

  associated with wings · CPC title

• B64D29/08 Primary

  Inspection panels for power plants · CPC title

• B64D27/12 Primary

  within, or attached to, wings · CPC title