Aircraft propulsion assembly having a device for reacting thrust forces

Patent metadata

Field	Value
Publication number	US-12337980-B2
Application number	US-202318471721-A
Country	US
Kind code	B2
Filing date	Sep 21, 2023
Priority date	Sep 23, 2022
Publication date	Jun 24, 2025
Grant date	Jun 24, 2025

Abstract

A propulsion assembly for an aircraft, having a turbomachine, a pylon, and a device for reacting thrust forces having a main fitting, a spreader pivoting on the main fitting and having an opening, two rods articulated to the turbomachine and to the spreader, a secondary fitting fastened beneath the pylon and having a secondary female clevis constituted of two secondary arms passed through by holes of oblong shape and aligned along a secondary axis (R 2 ), wherein the spreader is housed in the secondary female clevis of the secondary fitting, wherein the opening is coaxial with the secondary axis (R 2 ), and a backup connection pin inserted with a tight fit into the opening and with clearance into the holes. Also an aircraft with such a propulsion assembly.

First claim

The invention claimed is:

1. A propulsion assembly for an aircraft, said propulsion assembly having a median vertical plane and comprising:
a turbomachine,
a pylon,
at the front, a front engine attachment fastening the turbomachine to the pylon,
at the rear, a rear engine attachment fastening the turbomachine to the pylon, and
a device for reacting thrust forces comprising:
a main fitting fastened beneath the pylon,
a spreader mounted so as to be able to pivot on the main fitting about a main axis and having an opening,
two rods for reacting the thrust forces of an engine that are disposed on either side of the median vertical plane, each rod having a front end articulated to the turbomachine and a rear end articulated to the spreader, wherein each rod has a longitudinal axis, wherein the two longitudinal axes define a mean plane for transmission of the thrust forces, wherein the main axis is orthogonal to the mean plane for transmission of the thrust forces and comprised in the median vertical plane, wherein the rear end of each rod is articulated to the spreader about a front connection axis parallel to the main axis and wherein the two front connection axes are symmetrical with respect to the median vertical plane,
a secondary fitting fastened beneath the pylon in front of the main fitting and having a secondary female clevis constituted of two secondary arms, each one being passed through by a hole of oblong shape wherein the two holes are aligned along a secondary axis included in the mean plane for transmission of the thrust forces and perpendicular to the median vertical plane, and wherein a major axis of each hole is included in the mean plane for transmission of the thrust forces and perpendicular to the secondary axis, wherein the spreader is housed in the secondary female clevis of the secondary fitting, wherein the opening is coaxial with the secondary axis, and
a backup connection pin inserted with a tight fit into the opening and with clearance into the holes
wherein the main fitting comprises a central flange passed through by a through-bore coaxial with the main axis,
wherein the spreader has a female rear clevis into which the central flange is introduced,
wherein the female rear clevis comprises two rear arms wherein each one is passed through by a rear bore coaxial with the main axis,
wherein the device for reacting thrust forces has a rear connection pin fitted in the through-bore of the central flange and the rear bores of the female rear clevis,
wherein, for each rod, the spreader has a female front clevis into which the rear end of said rod, which is passed through by a through-bore coaxial with the corresponding front connection axis, is introduced,
wherein each female front clevis is constituted of two front arms and each one is passed through by a front bore coaxial with the corresponding front connection axis, and
wherein for each rod, the device for reacting thrust forces has a front connection pin fitted in the through-bore of said rod and in the front bores of the female front clevis.

2. The propulsion assembly according to claim 1 , wherein the rear engine attachment is articulated to the main fitting.

3. The propulsion assembly according to claim 1 , wherein the spreader has a body and two flanks,
wherein the body is passed through by the opening and has the rear arms and the front arms,
wherein each flank bears externally against a rear arm and a front arm of each female front clevis,
wherein for each rear bore, the flank adjoining the rear arm corresponding to said rear bore is passed through by a rear secondary bore coaxial with said rear bore,
wherein the rear connection pin also passes through the rear secondary bores of the flanks,
wherein for each front bore of a female front clevis, the flank adjoining the front arm corresponding to said front bore is passed through by a front secondary bore coaxial with said front bore, and
wherein the front connection pin also passes through the front secondary bores of the flanks.

4. An aircraft comprising:
a wing, and
the propulsion assembly according to claim 1 , wherein the pylon is fastened beneath the wing.

Assignees

• Airbus Operations Sas

Inventors

• Berjot Michael
• Gueneau Germain
• Combes Pierre-Antoine
• Taveau Paul-Adrien

Classifications

• B64D27/404

  Suspension arrangements specially adapted for supporting vertical loads · CPC title

• B64D27/40

  Arrangements for mounting power plants in aircraft · CPC title

• B64D27/406 Primary

  Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links · CPC title

• F05D2260/311

  of the frangible or shear type · CPC title

• F05D2240/91

  on a stationary structure · CPC title