Granted Patent B2

US 12,637,222 · App. 18/761,958 · Granted May 26, 2026

Inventors: Pierre-Antoine Combes (Toulouse, FR); Marc De Nicola (Toulouse, FR); Germain Gueneau (Toulouse, FR); Olivier Pautis (Toulouse, FR)

Assignee: AIRBUS OPERATIONS SAS

B64D27/402B64C3/32B64D27/40B64D27/404B64D29/06B64D27/18

Abstract

Claims (23)

1 . A propulsion system of an aircraft, said propulsion system comprising:

a turbojet extending around a longitudinal axis and having a vertical median plane passing through the longitudinal axis and having a fan casing with a rear face perpendicular to the longitudinal axis,

a pylon presenting a rigid structure with a front wall and a lower spar, and

an engine attachment comprising a front ring coaxial with the longitudinal axis and comprising first fixation means for securing the front ring to the rear face of the fan casing and second fixation means for securing the front ring to the front wall of the pylon,

wherein the engine attachment has a rear ring and a junction beam attached between the front ring and the rear ring,

wherein the rear ring is coaxial with the longitudinal axis, and is arranged at the rear of the front ring, and is attached to the lower spar,

wherein the pylon has a first rib which is fixed inside the rigid structure at a fixation between the rear ring and the lower spar.

2 . The propulsion system according to claim 1 , wherein the front ring comprises of an upper half ring attached to the pylon and a lower half ring attached to the junction beam,

wherein the rear ring comprises an upper half ring attached to the pylon and a lower half ring attached to the junction beam, and

wherein the engine attachment has two connecting rods arranged on either side of the vertical median plane where each is mounted articulated between the two upper half rings.

3 . The propulsion system according to claim 1 , wherein the engine attachment has two rear connecting rods arranged on either side of the vertical median plane where each is mounted hinged between a rear ring and the lower spar.

4 . The propulsion system according to claim 3 , wherein the pylon has a second rib which is attached inside the pylon at a fixation between the two rear connecting rods and the lower spar.

5 . The propulsion system according to claim 1 , wherein the first fixation means have two upper joints and two lower joints, wherein the two upper joints are arranged on either side of the vertical median plane and in an upper part of the front ring, and wherein the two lower joints are arranged on either side of the vertical median plane and in a lower part of the front ring.

6 . The propulsion system according to claim 5 , wherein each upper joint forms a pivot connection around an axis parallel to a transverse axis perpendicular to the median plane, and

wherein each lower joint forms a pivot link around an axis parallel to a vertical axis inscribed in the vertical median plane and perpendicular to the longitudinal axis.

7 . The propulsion system according to claim 1 , further comprising:

a nacelle comprising two shells attached to each other and to the rear of the fan casing where the two shells are joined to the front ring.

8 . The propulsion system according to claim 7 , wherein each shell has an upper wall,

wherein the upper walls face each other and each constitutes a lateral wall of the pylon, and

wherein the two upper walls are fixed on either side of the lower spar.

9 . An aircraft comprising:

a wing, and

the propulsion system according to claim 1 , wherein the rigid structure of which is fixed under the wing.

Assignments (1)

Priority Claims (1)

Continuity (3)

References Cited (56)