Sidewall panel assembly and return air bridge for use in an aircraft assembly

Patent metadata

Field	Value
Publication number	US-10220931-B2
Application number	US-201514935788-A
Country	US
Kind code	B2
Filing date	Nov 9, 2015
Priority date	Nov 9, 2015
Publication date	Mar 5, 2019
Grant date	Mar 5, 2019

Abstract

A return air bridge for use in an aircraft assembly includes an inboard portion configured to couple to a sidewall assembly at a bottom edge of the sidewall assembly and an outboard portion configured to couple to a structural member. The return air bridge also includes at least one support coupling the inboard portion to the outboard portion such that a return air flow path is defined between the inboard portion and the outboard portion. The outboard portion comprises a plate configured to direct an air flow along the return air flow path upwardly with respect to the bottom edge of the sidewall assembly.

First claim

What is claimed is:

1. A return air bridge for use in an aircraft assembly, said return air bridge comprising:
an inboard portion configured to couple to a sidewall assembly at a bottom edge of the sidewall assembly;
an outboard portion comprising a plate and an attachment mechanism extending from said plate and a flange extending from said plate proximate said attachment mechanism, said attachment mechanism positioned outboard of said inboard portion, and said attachment mechanism and said flange configured to couple to a structural member of an aircraft; and
at least one support coupling said inboard portion to said outboard portion such that said inboard portion is horizontally offset from said outboard portion, wherein a return air flow path is defined between said inboard portion and said outboard portion, wherein said plate is configured to direct an air flow along the return air flow path upwardly with respect to the bottom edge of the sidewall assembly.

2. The return air bridge in accordance with claim 1 , wherein said outboard portion further comprises a noise attenuating material coupled to an inboard side of said plate along the return air flow path.

3. The return air bridge in accordance with claim 1 , wherein said attachment mechanism extends directly from said plate.

4. The return air bridge in accordance with claim 3 , wherein said attachment mechanism comprises at least one of a clip, a clamp, a threaded fastener, or a pin.

5. The return air bridge in accordance with claim 3 , wherein the structural member comprises a portion of a floor panel.

6. The return air bridge in accordance with claim 1 , wherein the return air bridge spaces the bottom edge of the sidewall assembly a distance from the structural panel to define a gap therebetween.

7. The return air bridge in accordance with claim 1 , wherein said flange is obliquely oriented with respect to said plate, wherein said flange is positioned inboard of said attachment mechanism.

8. The return air bridge in accordance with claim 7 , wherein said flange extends from said plate such that said flange and said attachment mechanism define a gap therebetween configured to receive a portion of said structural member.

9. The return air bridge in accordance with claim 1 , wherein said plate is oriented within a range of 30 degrees to 60 degrees with respect to the structural panel.

10. The return air bridge in accordance with claim 1 , wherein at least a portion of said plate horizontally overlaps at least a portion of said inboard portion.

11. The return air bridge in accordance with claim 1 , wherein said outboard portion is positioned entirely outboard from an innermost edge of said inboard portion.

12. An aircraft assembly comprising:
a floor panel comprising an upward extending portion;
a sidewall assembly comprising a bottom edge and a grill; and
a return air bridge coupled between said floor panel and said grill, said return air bridge comprising:
an inboard portion coupled to said bottom edge of said sidewall assembly;
an outboard portion coupled to said floor panel, said outboard portion comprising a plate, said plate having a flange and an attachment mechanism that define a gap therebetween configured to receive said upward extending portion; and
at least one support coupling said inboard portion to said outboard portion such that a return air flow path is defined between said inboard portion and said outboard portion, wherein said outboard portion comprises a plate configured to direct an air flow along the return air flow path upwardly with respect to the bottom edge of said sidewall assembly.

13. The assembly in accordance with claim 12 , wherein said sidewall assembly comprises a sidewall and a decompression panel coupled between said sidewall and said return air bridge.

14. The assembly in accordance with claim 13 , wherein a bottom edge of said decompression panel defines said bottom edge of said sidewall assembly.

15. The assembly in accordance with claim 13 , wherein said decompression panel includes a film coupled to said grille such that said film covers an entirety of said grille.

16. A method of assembling an aircraft, said method comprising:
coupling an inboard portion of a return air bridge to a bottom edge of a sidewall assembly;
coupling an outboard portion of the return air bridge to a floor panel, wherein coupling the outboard portion comprises inserting a portion of the floor panel into a gap defined between a defined between a flange extending from a plate of the outboard portion and an attachment mechanism extending from the plate of the outboard portion; and
coupling a support member between the inboard portion and the outboard portion such that the inboard portion is horizontally offset from the outboard portion, wherein a return air flow path is defined between the inboard portion and the outboard portion, wherein the outboard portion includes a plate configured to direct an air flow along the return air flow path upwardly with respect to the bottom edge of the sidewall assembly.

17. The method in accordance with claim 16 , wherein the sidewall assembly includes a decompression panel having a bottom edge, and wherein coupling the inboard portion comprises coupling the inboard portion to the bottom edge of the decompression panel of the sidewall assembly.

18. The method in accordance with claim 17 , wherein the decompression panel includes a grille, the method further comprising coupling a film to the grille such that the film covers an entirety of the grille.

19. The method in accordance with claim 16 , further comprising coupling a noise attenuation material to the plate along the return air flow path.

20. The method in accordance with claim 16 , wherein the outboard portion includes an attachment mechanism, and wherein coupling the outboard portion comprises coupling the attachment mechanism of the outboard portion to the floor panel.

Assignees

• Boeing Co

Inventors

• Perkins Thomas Seth
• Hitchcock Cory Michael
• West John Erik
• Weston Adam R
• Tubbs Gregory A

Classifications

• B64C2001/009

  comprising decompression panels or valves for pressure equalisation in fuselages or floors · CPC title

• B64C1/066 Primary

  Interior liners · CPC title

• B64C1/40

  Sound or heat insulation {, e.g. using insulation blankets} · CPC title

• Y02T50/40

  Weight reduction · CPC title