Fire-fighting system for an aircraft, having a double-chamber reservoir

Patent metadata

Field	Value
Publication number	US-11389677-B2
Application number	US-202016842190-A
Country	US
Kind code	B2
Filing date	Apr 7, 2020
Priority date	Apr 12, 2019
Publication date	Jul 19, 2022
Grant date	Jul 19, 2022

Abstract

A fire-fighting system for an aircraft, the fire-fighting system having a reservoir having an exterior envelope which delimits an interior volume of the reservoir and an interior wall which extends inside the exterior envelope and separates the interior volume into a first chamber and a second chamber which are separate from one another and are each filled with an extinguishing fluid. A network of pipes, and a valve system are provided which are arranged so as to allow, in succession, the extinguishing fluid to flow from the first chamber to the network of pipes, and then the extinguishing fluid to flow from the second chamber to the network of pipes. Such a fire-fighting system allows simpler installation in the aircraft, the fitting of a single network of pipes and hence a saving in terms of weight and volume.

First claim

The invention claimed is:

1. A fire-fighting system for an aircraft, said fire-fighting system having:
a reservoir having an exterior envelope which delimits an interior volume of the reservoir and an interior wall which extends inside the exterior envelope and separates said interior volume into a first chamber and a second chamber which are separate from one another and are each filled with an extinguishing fluid,
a network of pipes, and
a valve system which is configured so as to allow, in succession, the extinguishing fluid to flow from the first chamber to the network of pipes, and then the extinguishing fluid to flow from the second chamber to the network of pipes, the valve system comprising:
a duct which has a first orifice opening into the first chamber, a second orifice opening into the second chamber, and a third orifice opening onto the network of pipes, said duct also having a first seat downstream of the second orifice and a second seat downstream of the first orifice,
a shut-off member configured to move between a first position in which the shut-off member is positioned on the first seat and a second position in which the shut-off member is positioned on the second seat,
a first disc which shuts off a passage between the first orifice and the third orifice,
a second disc which shuts off the passage between the second orifice and the shut-off member, and
for each disc, an opening system configured to destroy said disc when the operating system is activated.

2. The fire-fighting system according to claim 1 , wherein each chamber is fitted with a sensor configured to monitor a pressure of the extinguishing fluid in said chamber, and wherein the two sensors are connected to a same interface.

3. An aircraft comprising
an engine,
a pylon which bears the engine, and
a fire-fighting system for an aircraft, said fire-fighting system having:
a reservoir having an exterior envelope which delimits an interior volume of the reservoir and an interior wall which extends inside the exterior envelope and separates said interior volume into a first chamber and a second chamber which are separate from one another and are each filled with an extinguishing fluid,
a network of pipes, and
a valve system which is configured so as to allow, in succession, the extinguishing fluid to flow from the first chamber to the network of pipes, and then the extinguishing fluid to flow from the second chamber to the network of pipes, the valve system comprising:
a duct which has a first orifice opening into the first chamber, a second orifice opening into the second chamber, and a third orifice opening onto the network of pipes, said duct also having a first seat downstream of the second orifice and a second seat downstream of the first orifice,
a shut-off member configured to move between a first position in which the shut-off member is positioned on the first seat and a second position in which the shut-off member is positioned on the second seat,
a first disc which shuts off a passage between the first orifice and the third orifice,
a second disc which shuts off the passage between the second orifice and the shut-off member, and
for each disc, an opening system configured to destroy said disc when the operating system is activated,

wherein the reservoir is fixed in the pylon, and
wherein the network of pipes extends between said reservoir and the engine.

Assignees

• Airbus Operations Sas

Inventors

• Cayssials Julien
• Guichot Arnaud

Classifications

• A62C3/08 Primary

  in aircraft {(A62C3/0207 takes precedence)} · CPC title

• A62C35/023

  the extinguishing material being expelled by compressed gas, taken from storage tanks, or by generating a pressure gas (for foam generation A62C5/02) · CPC title

• A62C35/13

  with a finite supply of extinguishing material · CPC title

• A62C35/08

  Containers destroyed or opened by bursting charge · CPC title

• A62C35/68

  Details, e.g. of pipes or valve systems (valves in general F16K) · CPC title