Cooling device for the casing of an aircraft jet engine comprising a supporting device

Patent metadata

Field	Value
Publication number	US-9732885-B2
Application number	US-201414770209-A
Country	US
Kind code	B2
Filing date	Feb 25, 2014
Priority date	Feb 26, 2013
Publication date	Aug 15, 2017
Grant date	Aug 15, 2017

Abstract

A cooling device for the casing of a jet engine, includes a cooling tube and a supporting device, the supporting device including an attachment plate and an attachment clamp, the attachment clamp including a clamp body surrounding the cooling tube and an attachment element attached to the attachment plate, wherein the attachment plate includes: an opening; and an attachment tab secured to the main wall of the attachment plate and arranged on at one portion of the periphery of the opening, the attachment clamp passing through the opening, and the attachment element of the attachment clamp being attached to the attachment tab.

First claim

The invention claimed is:

1. A cooling device for a casing of a jet engine, said cooling device comprising at least one first cooling tube and at least one supporting device, the supporting device comprising an attachment plate and at least one first attachment clamp, the attachment plate being adapted to be rendered secure to the casing of the jet engine, the attachment plate comprising a main wall which has an external face and an internal face that are provided on two opposite sides of the main wall such that the external and internal faces are oriented to face in opposite directions, the first attachment clamp comprising a clamp body surrounding the first cooling tube and an attachment element attached to the attachment plate, the clamp body of the first attachment clamp being positioned on a side of the internal face of the main wall of the attachment plate,
wherein the attachment plate comprises:
at least one first opening;
at least one first attachment tab secured to said main wall of the attachment plate and arranged on at least one portion of a periphery of the first opening, the first attachment tab projecting from the external face of the main wall, the first attachment clamp passing through the first opening, the attachment element of said first attachment clamp being attached to the first attachment tab, and

wherein the cooling device further comprises a means of rigidifying the first attachment tab.

2. The cooling device as claimed in claim 1 , wherein the first attachment tab is substantially perpendicular to said main wall of the attachment plate.

3. The cooling device according to claim 1 , wherein the first attachment tab and the attachment plate form a single piece.

4. The cooling device according to claim 1 , wherein the main wall of the attachment plate has a first lateral edge and a second lateral edge, at least one of said first lateral edge and said second lateral edge being curved.

5. The cooling device as claimed in claim 1 , wherein the main wall of the attachment plate has a first lateral edge and a second lateral edge, wherein the means of rigidifying is formed by an extension, rendered secure to the first attachment tab, by at least one of said first lateral edge and second lateral edge.

6. The cooling device according to claim 1 , wherein the main wall of the attachment plate comprises several portions, two consecutive portions forming an angle between them.

7. The cooling device according to claim 1 , further comprising at least one second cooling tube consecutive to the first cooling tube, the supporting device further comprising
at least one second attachment clamp, the second attachment clamp comprising a clamp body surrounding the second cooling tube and an attachment element attached to the attachment plate;
wherein the main wall of the attachment plate comprises at least one second opening and at least one second attachment tab secured to said main wall of the attachment plate and arranged on at least one portion of a periphery of the second opening, the second attachment tab projecting from the external face of the main wall, the second attachment clamp passing through the second opening, the attachment element of said second attachment clamp being attached to the second attachment tab.

8. The cooling device as claimed in claim 7 , wherein the main wall of the attachment plate comprises a right portion and a left portion extending according to a length of the main wall, wherein the first attachment tab and the second attachment tab are consecutive and are respectively present on said right portion and on said left portion of the main wall of the attachment plate.

9. An aircraft comprising a jet engine with at least one casing, wherein said casing comprises a cooling device, said cooling device comprising at least one first cooling tube and at least one supporting device, the supporting device comprising an attachment plate and at least one first attachment clamp, the attachment plate comprising a main wall which has an external face and an internal face, the first attachment clamp comprising a clamp body surrounding the first cooling tube and an attachment element attached to the attachment plate, the clamp body of the first attachment clamp being positioned on a side of the internal face of the main wall of the attachment plate,
wherein the attachment plate comprises:
at least one first opening;
at least one first attachment tab secured to said main wall of the attachment plate and arranged on at least one portion of a periphery of the first opening, the first attachment tab projecting from the external face of the main wall, the first attachment clamp passing through the first opening, the attachment element of said first attachment clamp being attached to the first attachment tab, and

wherein the cooling device further comprises a means of rigidifying the first attachment tab.

10. The aircraft according to claim 9 , wherein the first attachment tab is substantially perpendicular to said main wall of the attachment plate.

11. The aircraft according to claim 9 , wherein the first attachment tab and the attachment plate form a single piece.

12. The aircraft according to claim 9 , wherein the main wall of the attachment plate has a first lateral edge and a second lateral edge, at least one of said first lateral edge and said second lateral edge being curved.

13. The aircraft according to claim 9 , wherein the main wall of the attachment plate has a first lateral edge and a second lateral edge, wherein the means of rigidifying is formed by an extension, rendered secure to the first attachment tab, by at least one of said first lateral edge and second lateral edge.

14. The aircraft according to claim 9 , wherein the main wall of the attachment plate comprises several portions, two consecutive portions forming an angle between them.

15. The aircraft according to claim 9 , wherein the cooling device further comprises at least one second cooling tube consecutive to the first cooling tube, the supporting device further comprising
at least one second attachment clamp, the second attachment clamp comprising a clamp body surrounding the second cooling tube and an attachment element attached to the attachment plate;
wherein the main wall of the attachment plate comprises at least one second opening and at least one second attachment tab secured to said main wall of the attachment plate and arranged on at least one portion of a periphery of the second opening, the second attachment tab projecting from the external face of the main wall, the second attachment clamp passing through the second opening, the attachment element of said second attachment clamp being attached to the second attachment tab.

16. The aircraft according to claim 15 , wherein the main wall of the attachment plate comprises a right portion and a left portion extending according to a length of the main wall, wherein the first attachment tab and the second attachment tab are consecutive and are respectively present on said right portion and on said left portion of the main wall of the attachment plate.

Assignees

• Snecma

Inventors

• Cohin Arthur
• Achbari Baghdad
• Charrie Audrey
• Massot Aurélien René-Pierre

Classifications

• F16L3/227 Primary

  each pipe being supported by a separate element fastened to the base · CPC title

• F01D11/24 Primary

  by selectively cooling-heating stator or rotor components · CPC title

• F16L53/70

  Cooling of pipes or pipe systems · CPC title

• F16L3/221

  having brackets connected together by means of a common support · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title