Aircraft engine attachment comprising inclined fixing elements, aircraft comprising said engine attachment and method for fixing an engine to an aircraft pylon using said engine attachment

Patent metadata

Field	Value
Publication number	US-11345479-B2
Application number	US-201916363513-A
Country	US
Kind code	B2
Filing date	Mar 25, 2019
Priority date	Apr 11, 2018
Publication date	May 31, 2022
Grant date	May 31, 2022

Abstract

An engine attachment configured to link an engine and an aircraft pylon comprising a first end fitting having two mutually parallel wings, a joining piece positioned between the first end fitting wings and linked to the first end fitting by a link system, fixing elements, linking the first end fitting and the pylon, including first and second fixing elements positioned between the first end fitting wings which are inclined by an angle of between 10 and 45° to be able to be put in place and removed in the presence of the joining piece linked to the first end fitting by the link system. The inclined fixing elements absorb lateral loads. The joining piece and the first end fitting are linked by the link system before the engine is fixed to the pylon. The engine is fixed to the pylon by putting the fixing elements in place.

First claim

The invention claimed is:

1. An assembly comprising an aircraft pylon attached to an engine by means of an engine attachment, the aircraft pylon comprising a vertical median plane separating the aircraft pylon into two symmetrical parts from each other, the engine attachment configured to link the engine and the aircraft pylon, the engine attachment comprising:
a first end fitting having a plate, configured to be pressed against a contact surface of the pylon, and two mutually parallel wings linked to the plate,
a joining piece, configured to be linked to the engine, positioned between the wings of the first end fitting and linked to the first end fitting by a first link system,
fixing elements, configured to link the first end fitting and the pylon, including first and second fixing elements positioned between the wings of the first end fitting,
for each of the fixing elements, through holes provided in the plate of the first end fitting,
wherein, for each of the first and second fixing elements, the through holes of the plate of the first end fitting have axes of revolution forming an angle of between 10 and 45° with the vertical median plane, in order for the first and second fixing elements to be able to be put in place and removed in a presence of the joining piece linked to the first end fitting by the first link system.

2. The engine attachment according to claim 1 , the engine attachment comprising a U-shaped reinforcement which has a base, pressed against the plate of the first end fitting, and two wings pressed against the wings of the first end fitting, characterized in that the reinforcement comprises, for each of the first and second fixing elements, a through hole having an axis of revolution aligned with that of a corresponding through hole of the plate of the first end fitting.

3. The engine attachment according to claim 2 , wherein the reinforcement comprises, for each of the first and second fixing elements, a boss having a bearing surface which surrounds the through hole of the reinforcement and which is at right angles to the axis of revolution of the through hole of the reinforcement.

4. The engine attachment according to claim 2 , wherein the reinforcement comprises a single boss having, for each of the first and second fixing elements, a bearing surface which surrounds the through hole of the reinforcement and which is at right angles to the axis of revolution of the through hole of the reinforcement.

Assignees

• Airbus Operations Sas

Inventors

• Geliot Jean
• Deforet Thomas
• Soulie Adeline
• Dubois Olivier

Classifications

• B64D27/404 Primary

  Suspension arrangements specially adapted for supporting vertical loads · CPC title

• B64D27/26 Primary

  Operations & Transport · mapped topic

• B64D2027/266

  Operations & Transport · mapped topic

• B64D27/40 Primary

  Arrangements for mounting power plants in aircraft · CPC title