Aircraft engine assembly comprising rear engine attachments in the form of shackles

Patent metadata

Field	Value
Publication number	US-10189575-B2
Application number	US-201615357106-A
Country	US
Kind code	B2
Filing date	Nov 21, 2016
Priority date	Nov 27, 2015
Publication date	Jan 29, 2019
Grant date	Jan 29, 2019

Abstract

An aircraft engine assembly including a set of rear engine attachments comprising a first shackle hinged on a bracket secured to the engine and on a bracket made as one piece with one of the two side panels, the shackle being oriented along a vertical direction, a second shackle hinged on a bracket secured to the engine and on a bracket made as one piece with the other one of the two side panels, the second shackle being oriented along the vertical direction, and a third shackle for transversally transmitting loads, inclined relative to the vertical direction and hinged on a bracket secured to the engine and on a bracket secured to the primary structure.

First claim

The invention claimed is:

1. An aircraft engine assembly comprising:
an engine,
a pylon for mounting the engine on a structure of the aircraft,
the pylon comprising a primary structure forming a box formed by lower spar and upper spars joined together by a plurality of transverse stiffening ribs situated inside the box, the box being closed laterally by two side panels,

means for mounting the engine on the primary structure of the mounting pylon, wherein the mounting means include a set of rear engine attachments comprising:
a first shackle hinged at one of its ends on a bracket secured to the engine and hinged at the other end on a bracket made as one piece with one of the two side panels, the first shackle being oriented along a vertical direction of the engine assembly and hinged on its associated brackets along hinging axes oriented along a transverse direction of the engine assembly;
a second shackle hinged at one of its ends on a bracket secured to the engine and hinged at the other end on a bracket made as one piece with the other one of the two side panels, the second shackle being oriented along the vertical direction of the engine assembly and hinged on its associated brackets along hinging axes oriented along the transverse direction of the engine assembly, the first and second shackles being arranged so as to be crossed by a vertical and transverse plane of the engine assembly; and
a third shackle for transverse transmission of the loads, inclined relative to the vertical direction and crossed by the vertical and transverse plane, the third shackle being hinged at one of its ends on a bracket secured to the engine and hinged at the other end on a bracket secured to the primary structure of the pylon.

2. The aircraft engine assembly according to claim 1 , wherein the third shackle is inclined at about 30° to 60° relative to the vertical direction.

3. The aircraft engine assembly according to claim 1 , wherein the third shackle is hinged on associated brackets along hinging axes oriented along a longitudinal direction of the engine assembly.

4. The aircraft engine assembly according to claim 1 , wherein, for each of the first and second shackles, the end which is hinged on the shackle made as one piece with the associated side panel, is also hinged on an additional bracket secured to the primary structure of the pylon, the bracket and the additional bracket facing each other so as to form a clevis.

5. The aircraft engine assembly according to claim 4 , wherein the additional bracket is made as one piece with one of the transverse stiffening ribs of the box.

6. The aircraft engine assembly according to claim 1 , wherein the bracket secured to the primary structure of the pylon, on which the third shackle is hinged, is made as one piece with one of the transverse stiffening ribs of the box.

7. The aircraft engine assembly according to claim 1 , wherein the bracket secured to the primary structure of the pylon, on which the third shackle is hinged, is made as one piece with one of the transverse stiffening ribs of the box and is in the form of a clevis.

8. The aircraft engine assembly according to claim 1 , wherein the first, second and third shackles are joined to an exhaust casing of the engine.

9. The aircraft engine assembly according to claim 1 , wherein the set of rear engine attachments also comprises at least one safety shackle which is only stressed in the event of a faulty condition of at least one of the first, second and third shackles.

10. The aircraft engine assembly according to claim 9 , wherein at least one safety shackle intersects the third shackle so as to form an X-shaped assembly in rear view.

11. The aircraft engine assembly according to claim 1 , wherein the mounting means also comprise a front engine attachment as well as a device for transmission of the thrust loads oriented along the longitudinal direction of the engine assembly.

12. The aircraft engine assembly according to claim 11 , wherein the set of rear engine attachments, the front engine attachment and the thrust load transmission device are engine mounting means forming an isostatic load transmission system.

13. The aircraft engine assembly according to claim 11 , wherein the thrust load transmission device comprises:
a support element fixed to the box on the outside of the latter;
two side rods for transmission of the thrust loads; and
a rudder bar hinged on the support element, the two side rods being hinged on the two opposite ends of the rudder bar, respectively.

14. The aircraft engine assembly according to claim 13 , wherein the support element is arranged at the front in relation to the set of rear engine attachments.

15. The aircraft engine assembly according to claim 1 , wherein the engine is a twin-shaft turbofan engine.

16. An aircraft comprising:
at least one engine assembly comprising:
an engine,
a pylon for mounting the engine on a structure of the aircraft,
the pylon comprising a primary structure forming a box formed by lower spar and upper spars joined together by a plurality of transverse stiffening ribs situated inside the box, the box being closed laterally by two side panels,
means for mounting the engine on the primary structure of the mounting pylon, wherein the mounting means include a set of rear engine attachments comprising:
a first shackle hinged at one of its ends on a bracket secured to the engine and hinged at the other end on a bracket made as one piece with one of the two side panels, the first shackle being oriented along a vertical direction of the engine assembly and hinged on its associated brackets along hinging axes oriented along a transverse direction of the engine assembly;
a second shackle hinged at one of its ends on a bracket secured to the engine and hinged at the other end on a bracket made as one piece with the other one of the two side panels, the second shackle being oriented along the vertical direction of the engine assembly and hinged on its associated brackets along hinging axes oriented along the transverse direction of the engine assembly, the first and second shackles being arranged so as to be crossed by a vertical and transverse plane of the engine assembly; and
a third shackle for transverse transmission of the loads, inclined relative to the vertical direction and crossed by the vertical and transverse plane, the third shackle being hinged at one of its ends on a bracket secured to the engine and hinged at the other end on a bracket secured to the primary structure of the pylon.

Assignees

• Airbus Operations Sas

Inventors

• Ewens David
• Blanc Jonathan
• Belloc Yves

Classifications

• B64D27/26 Primary

  Operations & Transport · mapped topic

• B64C3/32

  specially adapted for mounting power plant · CPC title

• B64D27/18 Primary

  within, or attached to, wings · CPC title

• B64D2027/266

  Operations & Transport · mapped topic

• B64D2027/268

  Operations & Transport · mapped topic