Decompression assembly with two decompression openings

Patent metadata

Field	Value
Publication number	US-10494077-B2
Application number	US-201615349254-A
Country	US
Kind code	B2
Filing date	Nov 11, 2016
Priority date	Nov 20, 2015
Publication date	Dec 3, 2019
Grant date	Dec 3, 2019

Abstract

An aircraft decompression assembly, comprising a cabin lining element, an element opening and an air channel adjacent to an element rear face and connected to the opening. A channel outlet, during normal assembly operation, discharges air exiting a cabin region delimited by the element through the opening into a secluded area between the element and an aircraft outer skin. A first decompression opening has a first decompression flap, which during normal operation, closes the first decompression opening and, in the event of a rapid decompression, opens the first decompression opening equalizing a pressure between the cabin region and the secluded area. A second decompression opening in the lining element has a second decompression flap which, during normal operation, closes the second decompression opening and which, in the event of a rapid decompression, opens the second decompression opening equalizing a pressure between the cabin region and the secluded area.

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,
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,

a second decompression opening formed in the cabin lining element, and
a second decompression flap which, during normal operation of the decompression assembly, is adapted to close the second decompression opening formed in the cabin lining element 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,
wherein the first decompression flap is biased into its closed position by means of a spring mechanism, and the first decompression flap, during normal operation of the decompression assembly, is locked in its closed position by means of a first locking mechanism, wherein the first locking mechanism is adapted to lock the first decompression flap in 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
wherein the spring mechanism is adapted to bias the first decompression flap, after a rapid decompression event, back into its closed position and back into engagement with the first locking mechanism as soon as the 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 is lower than the rapid decompression threshold value.

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 1 , wherein the second decompression opening is formed in a region of the cabin lining element which, when the cabin lining element is mounted in an aircraft cabin, faces away from a floor of the aircraft cabin, and wherein the opening is formed in a region of the cabin lining element which, when the cabin lining element is mounted in an aircraft cabin, faces the floor of the aircraft cabin.

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

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 away from the rear face of the cabin lining element so as to allow an airflow from the aircraft cabin region delimited by the cabin lining element through the second decompression opening into the aircraft area located between the cabin lining element and the aircraft outer skin.

9. The decompression assembly according to claim 8 , wherein the second pivot axis of the second decompression flap is attached to the rear face of the cabin lining element.

10. The decompression assembly according to claim 8 , wherein the second decompression flap, during normal operation of the decompression assembly, is locked in its closed position by means of a second locking mechanism.

11. The decompression assembly according to claim 10 , wherein the second locking mechanism further comprises a lever element which is adapted to be brought into contact with the second decompression flap, after a rapid decompression event, by a manual operation so as to move the second decompression flap back into its closed position and into engagement with the second locking mechanism.

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

13. A decompression assembly for use in an aircraft, the decompression assembly comprising:
a cabin lining element,
an opening formed in the cabin lining element,
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,

a second decompression opening formed in the cabin lining element, and
a second decompression flap which, during normal operation of the decompression assembly, is adapted to close the second decompression opening formed in the cabin lining element 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 locate

Assignees

• Airbus Operations Gmbh

Inventors

• Schneider Uwe

Classifications

• B64C1/18 Primary

  Floors · CPC title

• B64C1/066

  Interior liners · CPC title

• B64C2001/009

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

• B64D13/04

  Automatic control of pressure · 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