Decompression assembly with an air channel

Patent metadata

Field	Value
Publication number	US-10377462-B2
Application number	US-201615349244-A
Country	US
Kind code	B2
Filing date	Nov 11, 2016
Priority date	Nov 20, 2015
Publication date	Aug 13, 2019
Grant date	Aug 13, 2019

Abstract

A decompression assembly for use in an aircraft comprises a cabin lining element, an opening formed in the element, and an air channel arranged adjacent to a rear face of the element and connected to the opening. The air channel is provided with an air outlet which, during normal operation of the assembly, discharges air exiting a cabin region delimited by the element through the opening into an area located between the element and an aircraft outer skin, a first decompression opening, and a first decompression flap which, during normal operation of the decompression assembly, closes the first decompression opening in the air channel and which, in the event of a rapid decompression, opens the first decompression opening to allow a pressure equalization between the aircraft cabin region and the aircraft area located between the cabin lining element and the aircraft outer skin.

First claim

The invention claimed is:

1. A decompression assembly for use in an aircraft, the decompression assembly comprising:
a cabin lining element,
an opening formed in the cabin lining element, and
an air channel arranged adjacent to a rear face of the cabin lining element and connected to the opening formed in the cabin lining element,
wherein the air channel is provided with
an air outlet which, during normal operation of the decompression assembly, is adapted to discharge air exiting an aircraft cabin region delimited by the cabin lining element through the opening formed in the cabin lining element into an aircraft area located between the cabin lining element and an aircraft outer skin,
a first decompression opening, and
a first decompression flap which, during normal operation of the decompression assembly, is adapted to close the first decompression opening provided in the air channel and which, in the event of a rapid decompression, is adapted to open the first decompression opening so as to allow a pressure equalization between the aircraft cabin region delimited by the cabin lining element and the aircraft area located between the cabin lining element and the aircraft outer skin,

wherein the air channel further comprises:
a second decompression opening, and
a second decompression flap which, during normal operation of the decompression assembly, is adapted to close the second decompression opening provided in the air channel and which, in the event of a rapid decompression, is adapted to open the second decompression opening so as to allow a pressure equalization between the aircraft cabin region delimited by the cabin lining element and the aircraft area located between the cabin lining element and the aircraft outer skin.

2. The decompression assembly according to claim 1 , wherein the air outlet is formed in a first wall of the air channel which has a first edge facing the rear face of the cabin lining element and a second edge facing away from the rear face of the cabin lining element.

3. The decompression assembly according to claim 1 , wherein at least one of the opening formed in the cabin lining element and the air outlet formed in the air channel is covered by an air permeable grid.

4. The decompression assembly according to claim 1 , wherein the first decompression opening is formed in a second wall of the air channel which extends at a distance from the rear face of the cabin lining element opposed to the opening formed in the cabin lining element.

5. The decompression assembly according to claim 1 , wherein the first decompression flap is pivotable about a first pivot axis and, in the event of a rapid decompression, is adapted to pivot in a direction away from the rear face of the cabin lining element so as to allow an airflow from the air channel through the first decompression opening into the aircraft area located between the cabin lining element and the aircraft outer skin.

6. The decompression assembly according to claim 5 , wherein the first pivot axis of the first decompression flap is arranged along an edge of the first decompression flap which faces the air outlet.

7. The decompression assembly according to claim 1 , wherein the second decompression opening is formed in a third wall of the air channel which has a first edge facing the rear face of the cabin lining element and a second edge facing away from the rear face of the cabin lining element.

8. The decompression assembly according to claim 1 , wherein the second decompression flap is pivotable about a second pivot axis and, in the event of a rapid decompression, is adapted to pivot in a direction into an interior of the air channel so as to allow an airflow from the aircraft area located between the cabin lining element and the aircraft outer skin into the air channel through the second decompression opening.

9. The decompression assembly according to claim 8 , wherein the second pivot axis of the second decompression flap is arranged along an edge of the second decompression flap which faces away from the rear face of the cabin lining element.

10. The decompression assembly according to claim 1 , wherein a cross-sectional area of the first decompression opening is larger than a cross-sectional area of the second decompression opening.

11. The decompression assembly according to claim 1 , wherein at least one of the first decompression flap and the second decompression flap is biased into its closed position by means of a biasing mechanism.

12. The decompression assembly according to claim 11 , wherein the biasing mechanism is adapted to bias the at least one of the first decompression flap and the second decompression flap into its closed position until a pressure difference between the aircraft cabin region delimited by the cabin lining element and the aircraft area located between the cabin lining element and the aircraft outer skin exceeds a rapid decompression threshold value and further is adapted to bias the at least one of the first decompression flap and the second decompression flap, after a rapid decompression event, into its closed position again as soon as a pressure difference between the aircraft cabin region delimited by the cabin lining element and the aircraft area located between the cabin lining element and the aircraft outer skin again is lower than the rapid decompression threshold value.

13. The decompression assembly according to claim 1 , wherein the cabin lining element is a dado panel.

14. An aircraft comprising a decompression assembly comprising:
a cabin lining element,
an opening formed in the cabin lining element, and
an air channel arranged adjacent to a rear face of the cabin lining element and connected to the opening formed in the cabin lining element,
wherein the air channel is provided with
an air outlet which, during normal operation of the decompression assembly, is adapted to discharge air exiting an aircraft cabin region delimited by the cabin lining element through the opening formed in the cabin lining element into an aircraft area located between the cabin lining element and an aircraft outer skin,
a first decompression opening, and
a first decompression flap which, during normal operation of the decompression assembly, is adapted to close the first decompression opening provided in the air channel and which, in the event of a rapid decompression, is adapted to open the first decompression opening so as to allow a pressure equalization between the aircraft cabin region delimited by the cabin lining element and the aircraft area located between the cabin lining element and the aircraft outer skin,

wherein the air channel further comprises:
a second decompression opening, and
a second decompression flap which, during normal operation of the decompression assembly, is adapted to close the second decompression opening provided in the air channel and which, in the event of a rapid decompression, is adapted to open the second decompression opening so as to allow a pressure equalization between the aircraft cabin region delimited by the cabin lining element and the aircraft area located between the cabin lining element and the aircraft outer skin.

Assignees

• Airbus Operations Gmbh

Inventors

• Schneider Uwe

Classifications

• B64C1/18 Primary

  Floors · CPC title

• B64C2001/009

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

• B64C1/14 Primary

  Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens {accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers}(fairings movable in conjunction with undercarriage elements B64C25/16; bomb doors B64D1/06) · CPC title

• B64D13/04

  Automatic control of pressure · CPC title

• B64C1/066

  Interior liners · CPC title