Aircraft engine mount comprising at least one transverse nut and aircraft comprising the said engine mount

Patent metadata

Field	Value
Publication number	US-10183756-B2
Application number	US-201715641771-A
Country	US
Kind code	B2
Filing date	Jul 5, 2017
Priority date	Jul 8, 2016
Publication date	Jan 22, 2019
Grant date	Jan 22, 2019

Abstract

An aircraft engine mount which comprises first and second parts connected by connecting elements and wherein one of the two connected parts comprises at least one transverse hole opening onto an access face of the part and into which there open at least two passage holes each intended to house a threaded shank of one of the connecting elements. The engine mount comprises a transverse nut which comprises at least two bodies joined together each having a tapped hole configured to engage with one of the threaded shanks.

First claim

The invention claimed is:

1. An aircraft engine assembly connecting an engine to a pylon and comprising:
a first part secured to or forming part of a first of the elements that are the engine and the pylon,
a second part secured to or forming part of a second of the elements that are the engine and the pylon, wherein when one of the first part and the second part is secured to the engine or the pylon, the other of the first part and the second part is formed by the engine or the pylon,
at least two connecting elements each of which comprises a screw which comprises a head configured to bear against the first part in operation and a threaded shank,
the first and second parts each comprising a passage orifice for each of the at least two connecting elements,
the second part comprising at least one transverse hole opening onto an access face of the second part and into which there open at least two passage orifices, and

a nut configured to engage with one of the threaded shanks, the nut comprising a transverse nut which comprises at least two bodies joined together and which each comprise a tapped hole, the tapped holes of the nut having axes that substantially coincide with axes of the passage orifices in operation,
wherein the nut comprises a head at an end, and,
wherein the head comprises a wing configured to allow the nut to be grasped, the wing comprising an extension which projects beyond the access face of the second part and which comprises an edge face extending parallel to the axes of the tapped holes.

2. The aircraft engine assembly according to claim 1 , wherein the head is connected to one of the bodies of the at least two bodies.

3. The aircraft engine assembly according to claim 1 , wherein the head of the nut comprises a thrust surface configured to bear against the access face in operation.

4. The aircraft engine assembly according to claim wherein the head of the nut comprises a cylindrical portion with a diameter substantially equal to that of the transverse hole.

5. The aircraft engine assembly according to claim 1 , wherein the extension forms a thrust surface bearing against the access face in operation.

6. The aircraft engine assembly according to claim 1 , wherein the nut comprises at least one spacer piece configured to connect two bodies of the at least two bodies, the bodies and the at least one spacer piece or pieces being produced as a single piece.

7. The aircraft engine assembly according to claim 1 , wherein the nut comprises a support which comprises at least two housings each configured to accept a body of the at least two bodies.

8. The aircraft engine assembly according to claim 7 , wherein the support comprises the head and wherein the head forms a thrust surface configured to bear against the access face in operation.

9. An aircraft engine assembly connecting an engine to a pylon and comprising:
a first part secured to or forming part of a first of the elements that are the engine and the pylon,
a second part secured to or forming part of a second of the elements that are the engine and the pylon, wherein when one of the first part and the second part is secured to the engine or the pylon, the other of the first part and the second part is formed by the engine or the pylon,
connecting elements each of which comprises a screw which comprises a head configured to bear against the first part in operation and a threaded shank,
the first and second parts each comprising a passage orifice for each connecting element,
the second part comprising at least one transverse hole opening onto an access face of the second part and into which there open at least two passage orifices, and

a nut configured to engage with one of the threaded shanks, the nut comprising a transverse nut which comprises at least two bodies joined together and which each comprise a tapped hole, the tapped holes of the nut having axes that substantially coincide with axes of the passage orifices in operation, wherein the nut comprises a support which comprises at least two housings each configured to accept a body of the at least two bodies.

10. The aircraft engine assembly according to claim 9 , wherein the support comprises a head with a thrust surface configured to bear against the access face in operation.

11. The aircraft engine assembly according to claim 9 , wherein the nut at one of its ends comprises a head connected to one of the bodies of the at least two bodies.

12. The aircraft engine assembly according to claim 11 , wherein the head of the nut comprises a thrust surface configured to bear against the access face in operation.

13. The aircraft engine assembly according to claim 11 , wherein the head of the nut comprises a cylindrical portion with a diameter substantially equal to that of the transverse hole.

14. The aircraft engine assembly according to claim 11 , wherein the head comprises a wing configured to allow the nut to be grasped, the wing comprising an extension which projects beyond the access face of the second part and which comprises an edge face extending parallel to the axes of the tapped holes.

15. The aircraft engine assembly according to claim 14 , wherein the extension forms a thrust surface bearing against the access face in operation.

16. The aircraft engine assembly according to claim 9 , wherein the nut comprises at least one spacer piece configured to connect two bodies of the at least two bodies, the bodies and the at least one spacer piece or pieces being produced as a single piece.

Assignees

• Airbus Operations Sas

Inventors

• Journade Frederic
• Bouchet Eric
• Grosseau Nicolas
• Mutin Antoine

Classifications

• F16B37/047 Primary

  Barrel nuts · CPC title

• B64D2027/266

  Operations & Transport · mapped topic

• B64D27/26 Primary

  Operations & Transport · mapped topic

• B64D27/406

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

• B64D27/402

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