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

Patent metadata

Field	Value
Publication number	US-11518533-B2
Application number	US-202016878015-A
Country	US
Kind code	B2
Filing date	May 19, 2020
Priority date	May 21, 2019
Publication date	Dec 6, 2022
Grant date	Dec 6, 2022

Abstract

A front engine attachment system for an aircraft engine, the front engine attachment system having 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 has front, intermediate and rear plates. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. The intermediate plate is disposed between the front plate and the rear plate. Each link-rod system is fastened to the intermediate 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 a 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, an intermediate plate and a rear plate,
wherein the rear plate is pressed against the front face,
wherein the front plate is disposed in front of the rear plate, and
wherein the intermediate plate is disposed between the front plate and the rear plate,
wherein the front and rear plates contact the intermediate plate, and

wherein each link-rod system is fastened only to the intermediate 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,
wherein each link-rod system comprises a front link rod and a rear link rod,
wherein the front link rod and the rear link rod being mutually parallel,
wherein the front link rod being disposed in front of the rear link rod in a longitudinal direction,
wherein the front link rod and the rear link rod residing in a plane that is generally parallel to the front face of the attachment wall,
wherein each at least one first connection point between the beam and the link-rod system is formed as a clevis,
wherein one wall of said clevis is made up of the front link 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 intermediate plate is disposed between the front and rear link rods,
wherein a pin passes through a bore in each link rod and a bore in the intermediate plate,
wherein each link-rod system is fastened to the intermediate plate in an articulated manner by the at least one first connection point and is fastened to the front part of the engine in an articulated manner by at least one second connection point,
wherein each link-rod system is fastened only to the intermediate plate by the at least one first connection point,
wherein a first link-rod system is fastened to the intermediate plate by a first and a second first connection point and to the engine by one second connection point,
wherein a second link-rod system is fastened to the intermediate plate by a third first connection point and to the engine by another second connection point.

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 bolts, and
wherein each bolt passes through a bore in the attachment wall, a bore in the rear plate, a bore in the intermediate plate and a bore in the front plate.

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

4. The front engine attachment system according to claim 1 ,
wherein it 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 front plate and the rear plate constitute walls of the clevis,
wherein the engine is disposed between the front plate and the rear plate,
wherein a pin passes through a bore in the front plate, a bore in the engine and a bore in the rear plate, and
wherein a diameter of the bore in the engine is greater than the 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

• B64D27/26 Primary

  Operations & Transport · mapped topic

• B64D2027/268

  Operations & Transport · mapped topic

• B64D2027/264

  Operations & Transport · mapped topic

• B64D27/404 Primary

  Suspension arrangements specially adapted for supporting vertical loads · CPC title

• Y02T50/40

  Weight reduction · CPC title