Rear engine attachment for an aircraft engine

Patent metadata

Field	Value
Publication number	US-10647441-B2
Application number	US-201816192950-A
Country	US
Kind code	B2
Filing date	Nov 16, 2018
Priority date	Nov 21, 2017
Publication date	May 12, 2020
Grant date	May 12, 2020

Abstract

A rear engine attachment for an engine of an aircraft which comprises a pylon having a bottom face, the rear engine attachment comprising a first fitting configured to be fixed against the bottom face and having a wall, a second fitting configured to be secured to a structural casing of the engine, two front links and two rear links, which are fixed by one and the same main link point to the wall and by two link points on either side of the second fitting. Such a motorization assembly allows for a reduction of the bulk, in particular at the rear engine attachment, which helps in improving the overall performance of the motorization assembly.

First claim

The invention claimed is:

1. A rear engine attachment for an engine of an aircraft which comprises a pylon having a bottom face, the rear engine attachment comprising:
a first fitting configured to be fixed against the bottom face and comprising a wall which extends in a plane at right angles to a longitudinal axis X and having a front face configured to be oriented towards a front of the aircraft and a rear face configured to be oriented towards a rear of the aircraft,
a second fitting configured to be secured to a structural casing of the engine, the second fitting extending in a plane at right angles to the longitudinal axis X and having a front face configured to be oriented towards the front of the aircraft and a rear face configured to be oriented towards the rear of the aircraft,
a front inner link,
a rear inner link,
a front outer link, and
a rear outer link,
wherein the front inner link has a rear face which is positioned facing a front face of the wall and facing the front face of the second fitting,
wherein the rear inner link has a front face which is positioned facing a rear face of the wall and facing the rear face of the second fitting,
wherein the front outer link has a rear face which is positioned facing a front face of the front inner link,
wherein the rear outer link has a front face which is positioned facing a rear face of the rear inner link,
wherein the front inner link is fixed by a main link point to the wall and by a first link point and a second link point to the second fitting,
wherein the front outer link is fixed by the same main link point to the wall and by the same first link point and another second link point to the second fitting,
wherein the rear inner link is fixed by the same main link point to the wall and by the same first and the same second link points to the second fitting as the front inner link,
wherein the rear outer link is fixed by the same main link point to the wall and by the same first and the same second link points to the second fitting as the front outer link,
wherein at each of the link points, the four links and either the first or second fitting, are fixed by a common fixing element extending along an axis parallel to the longitudinal axis X.

2. The rear engine attachment according to claim 1 , wherein the main link point comprises a bore passing through the wall, a bore passing through each link and an axis which is fitted into the bore of each link and into the bore of the wall, wherein each link point to the second fitting comprises a bore passing through the second fitting, for each link associated with the link point, a bore passing through said link and an axis which is fitted into the bore of each link and into the bore of the second fitting.

3. The rear engine attachment according to claim 2 , wherein that the main link point is mounted without play, wherein each second link point is mounted without play, wherein the first link point is mounted with play at the second fitting, wherein the first link point is mounted without play at the front and rear inner links, and wherein the first link point is mounted with play at the front and rear outer links.

4. An aircraft comprising a pylon having a bottom face, an engine having a structural casing and a rear engine attachment according to claim 1 , wherein the first fitting is fixed against said bottom face, and wherein the second fitting is secured to the structural casing.

5. The rear engine attachment according to claim 1 , wherein each of the links is triangular in shape.

6. The rear engine attachment according to claim 5 , wherein each of the links has rounded edges.

7. The rear engine attachment according to claim 1 , wherein the inner links have a uniform thickness.

8. The rear engine attachment according to claim 2 , wherein at least one axis is hollow.

9. The rear engine attachment according to claim 2 , wherein the outer links further comprise extended portions, the extended portions being equal in depth to the inner links and extending in the direction of the first and second fittings.

10. The rear engine attachment according to claim 2 , wherein the axis which goes through the main link point is a double shear axis.

11. The rear engine attachment according to claim 2 , wherein axes which go through the first and second link points are single shear axes.

12. The rear engine attachment according to claim 2 , wherein the second link points pass through ball joint links in the second fitting.

13. The rear engine attachment according to claim 2 , wherein the main link point passes through a ball joint link in the first fitting.

14. The rear engine attachment according to claim 1 , wherein the main link point and the second link points, in combination with the links define a primary load path, and the first link point constitutes a standby safety fixing point.

15. The rear engine attachment according to claim 1 , wherein the first fitting is fixed against the bottom face by at least one bolt.

16. The rear engine attachment according to claim 2 , wherein the rear engine attachment takes the form of a double yoke joint.

17. The rear engine attachment according to claim 16 , wherein the double yoke joint has flanks which comprise the front links on one side and the rear links on the other side, wherein the wall and second fitting are both positioned between these flanks.

18. A rear engine attachment for an engine of an aircraft which comprises a pylon having a bottom face, the rear engine attachment comprising:
a first fitting configured to be fixed against the bottom face and comprising a wall which extends in a plane at right angles to a longitudinal axis X and having a front face configured to be oriented towards a front of the aircraft and a rear face configured to be oriented towards a rear of the aircraft,
a second fitting configured to be secured to a structural casing of the engine, the second fitting extending in a plane at right angles to the longitudinal axis X and having a front face configured to be oriented towards the front of the aircraft and a rear face configured to be oriented towards the rear of the aircraft,
a front inner link,
a rear inner link,
a front outer link, and
a rear outer link,
wherein the front inner link has a rear face which is positioned facing a front face of the wall and facing the front face of the second fitting,
wherein the rear inner link has a front face which is positioned facing a rear face of the wall and facing the rear face of the second fitting,
wherein the front outer link has a rear face which is positioned facing a front face of the front inner link,
wherein the rear outer link has a front face which is positioned facing a rear face of the rear inner link,
wherein the front inner link is fixed by a main link point to the wall and by a first link point and a second link point to the second fitting,
wherein the front outer link is fixed by the same main link point to the wall and by the same first link point and another second link point to the second fitting,
wherein the rear inner link is fixed by the same main link point to the wall and by the same first and the same second link points to the second fitting as the front inner link,
wherein the rear outer link is fixed by the same main link point to the wall and by the same first and the same second link points to the second fitting as the front outer link,
wherein the main link point comprises a bore passing through the wall, a bore passing through each link and an axis which is fitted into the bore of each lin

Assignees

• Airbus Operations Sas

Inventors

• Combes Stéphane
• Geliot Jean
• Deforet Thomas
• Soulie Adeline
• Orteu Benoit

Classifications

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F05D2240/90

  Mounting on supporting structures or systems · CPC title

• B64D2027/266

  Operations & Transport · mapped topic

• B64D2027/262

  Operations & Transport · mapped topic

• F02C7/20 Primary

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title