Engine pylon for fastening an aircraft engine

Patent metadata

Field	Value
Publication number	US-12337979-B2
Application number	US-202418626575-A
Country	US
Kind code	B2
Filing date	Apr 4, 2024
Priority date	Apr 6, 2023
Publication date	Jun 24, 2025
Grant date	Jun 24, 2025

Abstract

An engine pylon has a structure for fastening an aircraft engine beneath a wing and has two lateral faces. The structure has a tunnel laterally passing through it, between and through the lateral faces, and the engine pylon has a spreader housed in the tunnel and fastened in an articulated manner to each lateral face. A first end of the spreader has a first bore. A second end of the spreader has two second bores each forming a connection point with the engine. A rod is fastened in an articulated manner to the first bore and has two third bores each forming a connection point with the engine. Such an engine pylon has the ability to attach the engine, with reduced vertical bulk and with less drag.

First claim

The invention claimed is:

1. An engine pylon for fastening an engine of an aircraft, the engine pylon having:
a structure configured to be fastened beneath a wing of the aircraft and having two lateral faces, wherein the structure has a tunnel with two ends passing therethrough, wherein each of the two ends of the tunnel emerges at one of the two lateral faces,
a spreader housed in the tunnel and fastened in an articulated manner to each lateral face by a first connection point, wherein a first end of the spreader has a first bore, and wherein a second end of the spreader has two second bores each configured to form a second connection point with the engine, and
a rod fastened in an articulated manner to said first bore and having two third bores each configured to form a third connection point with the engine.

2. The engine pylon according to claim 1 ,
wherein each first connection point is constituted of a first female clevis fastened to an outside of a corresponding lateral face,
a single male clevis being constituted by the spreader,
wherein the spreader is disposed inside each first female clevis,
a first connection pin and a first ball joint ring being inserted and fastened in a bore of the spreader provided for such insertion, and
wherein the first connection pin is housed and fastened in the first ball joint ring and housed free to rotate in bores of the first female clevis provided for such rotatable housing.

3. The engine pylon according to claim 1 , wherein the rod is constituted of two shackles disposed on either side of the first end of the spreader,
wherein each of the third bores is constituted of a third sub-bore made in one of the shackles and a third sub-bore made in the other of the shackles,
wherein a third ball joint ring is inserted and fastened in the first bore of the spreader, and
wherein a third connection pin is housed and fastened in the third ball joint ring and housed free to rotate in a fourth sub-bore provided for such rotatable housing in each shackle.

4. An aircraft comprising:
a wing,
an engine having a structure and an engine pylon according to claim 1 ,
wherein the structure of the engine pylon is fastened beneath the wing,
wherein the two second bores each form a second connection point with the structure of the engine, and
wherein the two third bores each form a third connection point with the structure of the engine.

5. The aircraft according to claim 4 ,
wherein each second connection point is constituted of a second female clevis as one with the structure of the engine,
a single male clevis being constituted by the second end of the spreader,
wherein the spreader is disposed inside each second female clevis,
a second connection pin and a second ball joint ring being inserted and fastened in the second bore of the spreader, and
wherein the second connection pin is housed and fastened in the second ball joint ring and housed free to rotate in bores provided for such rotatable housing in the second female clevis.

6. The aircraft according to claim 4 ,
wherein the rod is constituted of two shackles disposed on either side of the first end of the spreader,
wherein each of the third bores is constituted of a third sub-bore made in one of the shackles and a third sub-bore made in the other of the shackles,
wherein a third ball joint ring is inserted and fastened in the first bore of the spreader,
wherein a third connection pin is housed and fastened in the third ball joint ring and housed free to rotate in a fourth sub-bore provided for such rotatable housing in each shackle,
wherein each third connection point is constituted of a pair of third female clevises as one with the structure of the engine,
for each third female clevis of the pair of third female clevises, a male clevis being constituted by one of the rods disposed inside said third female clevis,
a fourth connection pin and a fourth ball joint ring being inserted and fastened in the third sub-bores of each shackle, and
wherein the fourth connection pin is housed fastened in the fourth ball joint ring and housed free to rotate in the third sub-bores.

Assignees

• Airbus Operations Sas

Inventors

• Berjot Michael
• Combes Pierre-Antoine
• De Nicola Marc
• Vignes Jean-Baptiste

Classifications

• B64D27/404

  Suspension arrangements specially adapted for supporting vertical loads · CPC title

• B64D27/402 Primary

  comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant · CPC title

• B64D27/18 Primary

  within, or attached to, wings · CPC title