Propulsion system of an aircraft, having an asymmetrical nacelle
AssigneeAirbus Operations GmbH
InventorsPascal GOUGEON, Alexandre BELLANGER, Simon VANDERBAUWEDE
Life of this patent
Estimating the term…
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.
Claims6
A propulsion system for an aircraft, said propulsion system having a longitudinal axis and a vertical mid-plane passing through the longitudinal axis and 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 has:
- two inner cowls arranged around the core,
- two outer cowls arranged around the inner cowls,
- two lower structural elements, each fastening an inner cowl to an associated outer cowl at a bottom part of the nacelle, and
- two upper structural elements, each fastening an inner cowl to an associated outer cowl at a top part of the nacelle,
- wherein each outer cowl is mounted articulated on the pylon via hinges of which the axes 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 mid-plane, an acute angle counted positively in a clockwise direction in front view, and
- wherein the axis corresponding to a port-side outer cowl is disposed on a port side with respect to the separation plane, and wherein the axis corresponding to a starboard-side outer cowl is disposed on a starboard side with respect to an axis symmetrical to the axis corresponding to the port-side outer cowl with respect to the mid-plane.
A propulsion system for an aircraft, said propulsion system having a longitudinal axis and a vertical mid-plane passing through the longitudinal axis and 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 has:
- two inner cowls arranged around the core,
- two outer cowls arranged around the inner cowls,
- two lower structural elements, each fastening an inner cowl to the associated outer cowl at a bottom part of the nacelle, and
- two upper structural elements, each fastening an inner cowl to an associated outer cowl at a top part of the nacelle,
- wherein each outer cowl is mounted articulated on the pylon via hinges of which the axes 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 mid-plane, an acute angle counted positively in a counter-clockwise direction in front view, and
- wherein the axis corresponding to a starboard-side outer cowl is disposed on a starboard side with respect to the separation plane, and wherein the axis corresponding to a port-side outer cowl is disposed on a port side with respect to an axis symmetrical to the axis corresponding to the starboard-side outer cowl with respect to the mid-plane.
Dependencies are inferred from the claim text.