Aircraft fire suppression system and method

Patent metadata

Field	Value
Publication number	US-10343003-B2
Application number	US-201414504952-A
Country	US
Kind code	B2
Filing date	Oct 2, 2014
Priority date	Oct 2, 2014
Publication date	Jul 9, 2019
Grant date	Jul 9, 2019

Abstract

A fire suppression system for an aircraft having a compartment, the fire suppression system including an inert gas source in selective fluid communication with the compartment and a fire suppression agent source in selective fluid communication with the compartment, wherein an inert gas from the inert gas source and a fire suppression agent from the fire suppression agent source are at least partially combined to form a fire suppression mixture.

First claim

What is claimed is:

1. An aircraft comprising:
a cargo compartment; and
a fire suppression system comprising:
an inert gas source in selective fluid communication with said cargo compartment, said inert gas source supplying a first volume of an inert gas sufficient to achieve in said cargo compartment an added concentration of said inert gas ranging from about 15 percent to about 19 percent by volume; and
a fire suppression agent source in selective fluid communication with said cargo compartment, said fire suppression agent source supplying a second volume of a fire suppression agent, said fire suppression agent comprising at least one of 2-bromo-3,3,3-trifluoro-1-propene, 1,1,1,2,2-pentafluoroethane, and perfluoro(2-methyl-3-pentanone),
wherein said second volume of said fire suppression agent has a magnitude such that a fire suppression mixture comprising said first volume of said inert gas and said second volume of said fire suppression agent, when supplied to said cargo compartment, is effective against fire and prevents an explosion in an aerosol can explosion simulation test as said aerosol can explosion simulation test is defined in United States Federal Aviation Administration document DOT/FAA/TC-TN12/11 dated May, 2012.

2. The aircraft of claim 1 wherein said fire suppression system further comprises a nozzle positioned in said cargo compartment, wherein said fire suppression mixture is introduced to said cargo compartment by way of said nozzle.

3. The aircraft of claim 2 wherein said fire suppression system further comprises a conduit network comprising:
a main line fluidly coupled with said nozzle;
a first supply line fluidly coupling said inert gas source with said main line; and
a second supply line fluidly coupling said fire suppression agent source with said main line.

4. The aircraft of claim 3 wherein said fire suppression system further comprises:
a first flow control device on said first supply line; and
a second flow control device on said second supply line.

5. The aircraft of claim 4 wherein said fire suppression system further comprises a controller in communication with said first flow control device and said second flow control device, wherein said first flow control device and said second flow control device are actuatable by said controller.

6. The aircraft of claim 5 wherein said fire suppression system further comprises a fire detector in communication with said controller.

7. The aircraft of claim 5 wherein said fire suppression system further comprises a flight deck control in communication with said controller.

8. The aircraft of claim 3 wherein said cargo compartment comprises a forward compartment and an aft compartment, and wherein said main line is in fluid communication with said forward compartment and said aft compartment.

9. The aircraft of claim 8 wherein said fire suppression system further comprises at least one flow control device positioned on said main line to direct flow of said fire suppression mixture to at least one of said forward compartment and said aft compartment.

10. The aircraft of claim 1 wherein said inert gas source comprises at least one of a pressurized vessel, a solid propellant gas generator, and an on-board inert gas generation system.

11. The aircraft of claim 1 wherein said inert gas consists essentially of nitrogen.

12. The aircraft of claim 1 wherein said fire suppression agent source comprises a pressurized vessel.

13. The aircraft of claim 1 wherein said fire suppression agent comprises 2-bromo-3,3,3-trifluoro-1-propene.

14. A fire suppression system for an aircraft, said aircraft comprising a cargo compartment, said fire suppression system comprising:
a nozzle positioned in said cargo compartment;
a conduit network comprising:
a main line fluidly coupled with said nozzle;
a first supply line fluidly coupled with said main line; and
a second supply line fluidly coupled with said main line;

an inert gas source in fluid communication with said main line by way of said first supply line, said inert gas source supplying a first volume of inert gas sufficient to achieve an added concentration of said inert gas in said cargo compartment ranging from about 15 percent to about 19 percent by volume; and
a fire suppression agent source in fluid communication with said main line by way of said second supply line, said fire suppression agent source supplying a second volume of a fire suppression agent comprising at least one of 2-bromo-3,3,3-trifluoro-1-propene, 1,1,1,2,2-pentafluoroethane, and perfluoro(2-methyl-3-pentanone),
wherein said second volume of said fire suppression agent has a magnitude such that a fire suppression mixture comprising said first volume of said inert gas and said second volume of said fire suppression agent, when supplied to said cargo compartment, is effective against fire and prevents an explosion in an aerosol can explosion simulation test as said aerosol can explosion simulation test is defined in United States Federal Aviation Administration document DOT/FAA/TC-TN12/11 dated May, 2012.

15. The fire suppression system of claim 14 wherein said inert gas consists essentially of nitrogen.

16. The fire suppression system of claim 14 wherein said fire suppression agent comprises 2-bromo-3,3,3-trifluoro-1-propene.

17. The aircraft of claim 14 wherein said inert gas source comprises an on-board inert gas generation system.

18. A method for suppressing a fire in a cargo compartment of an aircraft, said method comprising:
monitoring said cargo compartment for presence of a fire; and
after said fire is detected, simultaneously introducing into said cargo compartment a first volume of an inert gas and a second volume of a fire suppression agent comprising at least one of 2-bromo-3,3,3-trifluoro-1-propene, 1,1,1,2,2-pentafluoroethane, and perfluoro(2-methyl-3-pentanone),
wherein said first volume has a magnitude that yields an added concentration of said inert gas in said cargo compartment ranging from about 15 percent to about 19 percent by volume, and
wherein said second volume has a magnitude such that a fire suppression mixture comprising said first volume of said inert gas and said second volume of said fire suppression agent, when supplied to said cargo compartment, is effective against fire and prevents an explosion in an aerosol can explosion simulation test, as said aerosol can explosion simulation test is defined in United States Federal Aviation Administration document DOT/FAA/TC-TN12/11 dated May, 2012.

19. The method of claim 18 further comprising issuing a warning when said fire is detected.

20. The method of claim 18 wherein said simultaneously introducing step is automatically performed when said fire is detected.

21. The method of claim 18 wherein said inert gas consists essentially of nitrogen.

22. The method of claim 18 wherein said fire suppression agent comprises 2-bromo-3,3,3-trifluoro-1-propene.

Assignees

• Boeing Co

Inventors

• Baker Patrick T
• Ferguson Douglas E
• Madden Mike R

Classifications

• A62C35/02

  with containers for delivering the extinguishing substance · CPC title

• A62C99/0018

  using gases or vapours that do not support combustion, e.g. steam, carbon dioxide · 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

• A62C3/08 Primary

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

• A62C37/36

  an actuating signal being generated by a sensor separate from an outlet device · CPC title