Engine pylon for coupling a jet engine to a wing of an aircraft

Patent metadata

Field	Value
Publication number	US-11465765-B2
Application number	US-202016933244-A
Country	US
Kind code	B2
Filing date	Jul 20, 2020
Priority date	Jul 31, 2019
Publication date	Oct 11, 2022
Grant date	Oct 11, 2022

Abstract

An engine pylon for mounting a jet engine beneath a wing of an aircraft, the engine pylon having a primary structure having two internal lateral fittings that face one another and a rib that is fastened between the two internal lateral fittings and a primary box that at least partially surrounds the primary structure and comprises a first part made from a composite material.

First claim

The invention claimed is:

1. An engine pylon for mounting a jet engine beneath a wing of an aircraft, the engine pylon comprising:
a primary structure having two internal lateral fittings that face one another and a rib that is fastened between the two internal lateral fittings;
a primary box that at least partially surrounds the primary structure and comprises a first part made from a composite material, wherein in a plane perpendicular to a longitudinal axis of the engine pylon, the first part has an inverted U-shaped section, with two lateral walls that are connected by an upper side so that the first part forms a monolithic structure;
a first and a second set of upper shackles, wherein the first set of upper shackles fastens, in use, a first lateral wall of the first part of the primary box and a first internal lateral fitting to a structural element of the wing, and in that the second set of upper shackles fastens, in use, a second lateral wall of the first part of the primary box and a second internal lateral fitting to a structural element of the wing; and,
a first and a second set of lower shackles, wherein the first set of lower shackles fastens, in use, the first lateral wall of the first part of the primary box and the first internal lateral fitting to a structural element of the wing, and in that the second set of lower shackles fastens, in use, the second lateral wall of the first art of the primary box and the second internal lateral fitting to a structural element of the wing,
wherein the first set of lower shackles are parallel with the first lateral wall of the first part of the primary box and the second set of lower shackles are parallel with the second lateral wall of the first part of the primary box.

2. The engine pylon according to claim 1 , wherein the primary box has a second part extending against free ends of the two lateral walls, and wherein, in the plane perpendicular to the longitudinal axis of the engine pylon, the primary box has a trapezoidal section.

3. The engine pylon according to claim 2 , wherein in the plane perpendicular to the longitudinal axis of the engine pylon, the upper side is longer than the second part.

4. The engine pylon according to claim 1 , wherein the upper shackles of the first and the second sets of upper shackles are oriented with an inclination of between 0° and 45° relative to a purely horizontal axis, and preferably they are oriented more or less horizontally.

5. The engine pylon according to claim 1 , wherein the upper shackles of the first and the second sets of upper shackles are each aligned in a continuation of the first and the second lateral walls, respectively, of the first part of the primary box.

6. The engine pylon according to claim 1 , wherein the lower shackles of the first and the second sets of lower shackles are oriented with an inclination of between 0° and 30° relative to a purely vertical axis.

7. The engine pylon according to claim 1 , wherein in a rear zone, two internal lateral fittings form a rear clevis, and wherein the engine pylon has a rear rod connecting, in use, the rear clevis to the wing.

8. The engine pylon according to claim 1 , wherein the engine pylon has a transverse shackle that is oriented in a transverse direction of the engine pylon and connects, in use, an internal lateral fitting to the wing, and wherein a line connecting centers of two apertures in the transverse shackle is oriented transversely relative to a longitudinal axis of the engine pylon.

9. The engine pylon according to claim 1 , wherein the engine pylon further comprises has an outer cowling having a shape of an inverted U and which covers the primary box.

10. The engine pylon according to claim 1 , wherein the first part has aerodynamic shapes, and wherein the engine pylon has a front cowling that extends the first part towards a front of the engine pylon, and a rear cowling that extends the first part towards a rear of the engine pylon.

11. An aircraft comprising:
a wing,
a jet engine, and
the engine pylon according to claim 1 fastened between the wing and the jet engine.

12. The engine pylon according to claim 1 , wherein the upper shackles of the first and the second sets of upper shackles are oriented more or less horizontally.

13. The engine pylon according to claim 1 , wherein the lower shackles of the first and the second sets of lower shackles are oriented more or less vertically.

Assignees

• Airbus Operations Sas

Inventors

• Blanc Jonathan
• Pautis Olivier

Classifications

• B64D27/18 Primary

  within, or attached to, wings · CPC title

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title

• B64D2027/264

  Operations & Transport · mapped topic

• B64D27/26 Primary

  Operations & Transport · mapped topic

• B64D27/402

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