Assembly for an aircraft including a fitting secured to the upper surface of a wing box, for mounting an engine strut to said wing box

Patent metadata

Field	Value
Publication number	US-10358226-B2
Application number	US-201615146686-A
Country	US
Kind code	B2
Filing date	May 4, 2016
Priority date	Nov 5, 2013
Publication date	Jul 23, 2019
Grant date	Jul 23, 2019

Abstract

In order to bring a turbofan engine closer to the lower surface of a wing box, the disclosure herein foresees an assembly for an aircraft including a mount for mounting a rigid structure of an engine strut to the wing box, the mount including an upper wing mount including a fitting secured to the upper surface of the wing box.

First claim

The invention claimed is:

1. An assembly for an aircraft including a wing element, a turbofan engine and an engine strut, the engine including a rear portion arranged below the wing element, the wing element having a wing box formed by a front spar and an upper surface of the wing element, the assembly further including a mount for mounting a rigid structure of the engine strut to the wing box,
the mount comprising an upper wing mount comprising a fitting secured to the upper surface of the wing element, and the rigid structure of the engine strut comprising a rear end at least partially embedded in a leading edge of the wing element, the rear end being located forward of the front spar,
wherein the mount of the rigid structure comprises wing mounts including:
the upper wing mount to transfer only thrust loads oriented in a longitudinal direction from the engine;
two lower wing mounts offset transversely from one another, and each configured to transfer only thrust loads oriented in the longitudinal direction and in a vertical direction from the engine; and
a lateral wing mount to transfer only forces oriented in a transversal direction from the engine.

2. The assembly according to claim 1 , wherein the rigid structure of the engine strut has at least one cross section of height greater than a height of the front spar.

3. The assembly according to claim 1 , wherein the rigid structure of the engine strut is located entirely above a low point of the wing element.

4. The assembly according to claim 1 , wherein the rigid structure of the engine strut has a front end secured to an outer ferrule of an intermediate casing of the engine, the outer ferrule extending in continuation of a fan casing.

5. The assembly according to claim 1 , wherein the engine is arranged so as to circulate a portion of the secondary airflow of the engine above the wing element.

6. The assembly according to claim 1 , wherein the mount forms an isostatic load transfer system.

7. The assembly according to claim 6 , wherein the upper wing mount comprises a connecting rod articulated on the fitting and oriented in the longitudinal direction.

8. The assembly according to claim 1 , wherein each of the two lower wing mounts has a fitting secured to the front spar of the wing box.

9. The assembly according to claim 1 , wherein the lateral wing mount comprises a connecting rod articulated at both ends on two fittings secured to a sidewall panel of the rigid structure of the engine strut, and to the front spar of the wing box.

10. An assembly for an aircraft including a wing element, a turbofan engine and an engine strut, the engine including a rear portion arranged below the wing element, the wing element having a wing box formed by a front spar and an upper surface of the wing element, the assembly further including a mount for mounting a rigid structure of the engine strut to the wing box,
the mount comprising an upper wing mount comprising a fitting secured to the upper surface of the wing element, and the rigid structure of the engine strut comprising a rear end at least partially embedded in a leading edge of the wing element, the rear end being located forward of the front spar,
wherein the mount of the rigid structure comprises wing mounts including:
the upper wing mount designed to transfer only thrust loads oriented in a longitudinal direction of the engine and in a transversal direction thereof; and
two lower wing mounts offset transversely from one another, and each designed to transfer only thrust loads oriented in the longitudinal direction and in a vertical direction from the engine.

11. The assembly according to claim 1 , wherein the rigid structure is shaped as a box.

12. An aircraft including at least one assembly according to claim 1 .

Assignees

• Airbus Operations Sas

Inventors

• Pautis Olivier

Classifications

• B64D27/18

  within, or attached to, wings · CPC title

• B64D27/26 Primary

  Operations & Transport · mapped topic

• B64D2027/264

  Operations & Transport · mapped topic

• B64D27/402 Primary

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

• B64D27/12 Primary

  within, or attached to, wings · CPC title