Front engine attachment system for an aircraft engine, having a beam made in three parts
US-2020385132-A1 · Dec 10, 2020 · US
Front engine attachment system for an aircraft engine, which has a compact structure
US11975857B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-11975857-B2 |
| Application number | US-202217899673-A |
| Country | US |
| Kind code | B2 |
| Filing date | Aug 31, 2022 |
| Priority date | Sep 3, 2021 |
| Publication date | May 7, 2024 |
| Grant date | May 7, 2024 |
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- Title
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Abstract
Official abstract text for this publication.
A front engine attachment system having an engine pylon having a frontal rib fastened against a front face, a front engine attachment having a beam fastened to the frontal rib, two rods articulated to the beam respectively via two connection points and one connection point, and a front casing of an engine, wherein the first rod is articulated to the front casing via a connection point and wherein the second rod is articulated to the front casing via a connection point, wherein each point of connection of a rod to the beam is positioned inside a volume that extends the front face of the engine pylon towards the front. Such a front engine attachment system has reduced bulk and therefore less drag.
First claim
Opening claim text (preview).
The invention claimed is: 1. A front engine attachment system for an engine of an aircraft, the front engine attachment system comprising: an engine pylon having a front face and a frontal rib fastened against the front face, a front engine attachment having a beam fastened to a front of the frontal rib, a first rod fastened in an articulated manner to the beam via two connection points and a second rod fastened in an articulated manner to the beam via one connection point, and a front casing of the engine, wherein the first rod is fastened in an articulated manner to the front casing via a connection point and wherein the second rod is fastened in an articulated manner to the front casing via a connection point, wherein each point of connection of a rod to the beam is positioned inside a volume that extends the front face of the engine pylon towards the front, wherein the volume is laterally delimited by a first plane on which a first lateral wall of the pylon lies and a second plane on which a second lateral wall of the pylon lies. 2. The front engine attachment system according to claim 1 , for each point of connection of a rod to the beam, the beam has a female clevis in which the rod is positioned. 3. The front engine attachment system according to claim 2 , wherein the beam is made up of a main plate, a secondary plate parallel to the main plate and a block forming a spacer between the main plate and the secondary plate, wherein the main plate is pressed against the frontal rib, and wherein, for each female clevis of the beam, one wall of said female clevis is formed by the main plate and another wall of said female clevis is formed by the secondary plate. 4. An aircraft comprising: 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 casing is as one with the engine.
Assignees
Inventors
Classifications
- F02C7/20Primary
Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title
Suspension arrangements specially adapted for supporting vertical loads · CPC title
comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant · CPC title
- B64D27/40Primary
Arrangements for mounting power plants in aircraft · CPC title
Weight reduction · CPC title
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- What does patent US11975857B2 cover?
- A front engine attachment system having an engine pylon having a frontal rib fastened against a front face, a front engine attachment having a beam fastened to the frontal rib, two rods articulated to the beam respectively via two connection points and one connection point, and a front casing of an engine, wherein the first rod is articulated to the front casing via a connection point and where…
- Who is the assignee on this patent?
- Airbus Operations Sas
- What technology area does this patent fall under?
- Primary CPC classification F02C7/20. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue May 07 2024 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 6 related publications on this page (citations in our corpus or others sharing the same primary CPC).