Propulsion system for an aircraft comprising a turbojet, a pylon and engine attachment
AssigneeAirbus Operations GmbH
InventorsPierre-Antoine Combes, Marc De Nicola, Germain Gueneau, Olivier Pautis
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Abstract
A propulsion system of an aircraft 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 element for securing the front ring to the rear face of the fan casing and second fixation element for securing the front ring to the front wall of the pylon.
Claims9
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.
Dependencies are inferred from the claim text.