Front engine attachment system for an aircraft engine, having a beam made in two parts

Patent metadata

Field	Value
Publication number	US-11535389-B2
Application number	US-202016878011-A
Country	US
Kind code	B2
Filing date	May 19, 2020
Priority date	May 21, 2019
Publication date	Dec 27, 2022
Grant date	Dec 27, 2022

Abstract

A front engine attachment system for an engine of an aircraft. The front engine attachment system has an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam fastened to the front face and to which a link-rod system is fastened on either side of a median plane. The beam is made up of a front plate and a rear plate that are fastened together in a removable manner. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. Each link-rod system is fastened to the rear plate in an articulated manner by at least one first connection point and is configured to be fastened to a front part of the engine in an articulated manner by at least one second connection point.

First claim

The invention claimed is:

1. A front engine attachment system for an engine of an aircraft, the front engine attachment system having:
an engine pylon having, in its front part, a frontal part having an attachment wall that has a front face, and
a front engine attachment having a beam that is fastened to the front face and to which a link-rod system is fastened on either side of a median plane,
wherein the beam is made up of a front plate and a rear plate that are fastened together in a removable manner,
wherein the rear plate is pressed against the front face and
wherein the front plate is disposed in front of the rear plate, and

wherein each link-rod system is fastened only to the rear plate in an articulated manner by at least one first connection point and is intended to be fastened to a front part of the engine in an articulated manner by at least one second connection point,
wherein each link-rod system comprises a front link rod and a rear link rod,
wherein each first connection point between the beam and a link-rod system is formed as a clevis, wherein one wall of said clevis is made up of the front rod of said link-rod system, wherein another wall of said clevis is made up of the rear link rod of said link-rod system,
wherein the rear plate is disposed between the front and rear link rods, and
wherein a pin passes through a bore in each link rod and a bore in the rear plate.

2. The front engine attachment system according to claim 1 ,
wherein the fastening of the beam to the front face of the attachment wall is realized by a pair of bolts disposed on a port side and a pair of bolts installed on a starboard side, and
wherein, for each pair of bolts, there is a first bolt, which is disposed in a top part and passes through a bore in the attachment wall and a bore in the rear plate, and a second bolt, which is disposed in a bottom part and passes through a bore in the attachment wall, a bore in the rear plate and a bore in the front plate.

3. The front engine attachment system according to claim 1 , wherein the rear plate is mounted on the pin via a ball joint connection.

4. The front engine attachment system according to claim 1 ,
wherein the front engine attachment system has, for each link-rod system, a backup safety fastening point that is activated upon a failure of a primary load path and creates an auxiliary load path between the engine and the engine pylon,
wherein each backup safety fastening point is made up of a clevis,
wherein the attachment wall and the front wall constitute walls of the clevis,
wherein the engine is disposed between the attachment wall and the front plate,
wherein a pin passes through a bore in the attachment wall, a bore in the engine and a bore in the front plate, and
wherein a diameter of the bore in the engine is greater than a diameter of the pin.

5. An aircraft having a structure, an engine and a front engine attachment system according to claim 1 ,
wherein the engine pylon is fastened to the structure, and
wherein the front part of the engine is fastened to said at least one second connection point.

Assignees

• Airbus Operations Sas

Inventors

• Deforet Thomas
• Lansiaux Rémi
• Dubois Olivier
• Puech Jacky

Classifications

• B64D27/402 Primary

  comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant · CPC title

• B64D2027/264

  Operations & Transport · mapped topic

• B64D27/26 Primary

  Operations & Transport · mapped topic

• B64D2027/268

  Operations & Transport · mapped topic

• B64D27/404

  Suspension arrangements specially adapted for supporting vertical loads · CPC title