Forward engine attachment system for an aircraft engine comprising a direct coupling between the jet engine pylon and the engine

Patent metadata

Field	Value
Publication number	US-11338929-B2
Application number	US-202016878346-A
Country	US
Kind code	B2
Filing date	May 19, 2020
Priority date	May 21, 2019
Publication date	May 24, 2022
Grant date	May 24, 2022

Abstract

A forward engine attachment system for an engine of an aircraft, the forward engine attachment system including a jet engine pylon including, in the region of the forward part thereof, a front part having an attachment wall, and a forward engine attachment with a connecting rod system on either side of a median plane, wherein each connecting rod system is fixed in articulated manner by at least one first link point to the attachment wall and is designed to be fixed in an articulated manner by at least one second link point to a forward part of the engine. Such a forward engine attachment system thus includes a direct coupling between the jet engine pylon and the engine, allowing the production of an assembly that is less heavy and is easier to produce.

First claim

The invention claimed is:

1. A forward engine attachment system for an engine of an aircraft, the forward engine attachment system comprising:
a jet engine pylon comprising, in a region of a forward part thereof, a front part having an attachment wall; and
a forward engine attachment comprising:
a first connecting rod system comprising:
a front connecting rod;
a rear connecting rod; and
a standby safety coupling point configured for activation upon a failure of a primary stress path of the first connecting rod system;
wherein the front and rear connecting rods are connected to, at one or more first link points, the attachment wall on opposite sides thereof in an articulated manner, in a form of a clevis at each of the one or more first link points;
wherein the front and rear connecting rods are configured for connection to, at one or more second link points, a forward part of the engine in an articulated manner;
wherein a first wall of each clevis is constituted by the forward connecting rod;
wherein a second wall of each clevis is constituted by the rear connecting rod;
wherein the attachment wall is positioned between the two connecting rods; and
wherein a bar traverses, at each of the one or more first link points, a bore formed through each of the first connecting rod, the second connecting rod, and the attachment wall; and

a second connecting rod system comprising:
a front connecting rod;
a rear connecting rod; and
a standby safety coupling point configured for activation upon a failure of a primary stress path of the second connecting rod system;
wherein the front and rear connecting rods are connected, at one or more first link points, to the attachment wall on opposite sides thereof in a form of a clevis;
wherein the front and rear connecting rods are configured for connection to, at one or more second link points, a forward part of the engine in an articulated manner
wherein a first wall of each clevis is constituted by the forward connecting rod;
wherein a second wall of each clevis is constituted by the rear connecting rod;
wherein the attachment wall is between the two connecting rods; and
wherein a bar traverses, at each of the one or more first link points, a bore formed through each of the first connecting rod, the second connecting rod, and the attachment wall;

wherein the first connecting rod system is on an opposite side of a median plane of the jet engine pylon from the second connecting rod system;
wherein each standby safety coupling is configured, when activated, to create an auxiliary stress path between the engine and the jet engine pylon; and
wherein each standby safety coupling point comprises a clevis produced in the engine and a bar, which is sleeved in bores of the clevis and traverses a bore of the attachment wall, a diameter of which is greater than a diameter of the bar.

2. The forward engine attachment system according to claim 1 , wherein, at each of the one or more first link points, the attachment wall is mounted on the bar by a swivel link.

3. The forward engine attachment system according to claim 1 , wherein the median plane extends in a vertical direction and in a longitudinal direction of the jet engine pylon.

4. An aircraft comprising:
a structure;
an engine; and
a forward engine attachment system according to claim 1 ;
wherein the jet engine pylon is fixed to the structure; and
wherein a forward part of the engine is fixed to the one or more second link points of each of the first and second connecting rod systems.

Assignees

• Airbus Operations Sas

Inventors

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

Classifications

• B64D27/404 Primary

  Suspension arrangements specially adapted for supporting vertical loads · CPC title

• B64D27/18

  within, or attached to, wings · CPC title

• B64D2027/266

  Operations & Transport · mapped topic

• B64D27/26 Primary

  Operations & Transport · mapped topic

• Y02T50/40

  Weight reduction · CPC title