Fire extinguishing discharge nozzle for helicopter engine compartment

Patent metadata

Field	Value
Publication number	US-11865382-B2
Application number	US-202117158496-A
Country	US
Kind code	B2
Filing date	Jan 26, 2021
Priority date	Jan 26, 2021
Publication date	Jan 9, 2024
Grant date	Jan 9, 2024

Abstract

Embodiments are directed to a rotorcraft comprising an airframe having an engine compartment, an engine disposed within the engine compartment, at least one fire bottle configured to hold a fire extinguishing agent, at least one agent tube coupled to the fire bottle and configured to carry the fire extinguishing agent to the engine compartment, and a nozzle on the at least one agent tube, the nozzle positioned above the engine and oriented in a downward-facing direction. The nozzle has at least one opening and is configured to allow liquid to drain out of the at least one opening instead of allowing the liquid to flow into the at least one agent tube. The nozzle may have a chamfer opening that faces downward.

First claim

What is claimed is:

1. A rotorcraft comprising:
an airframe having an engine compartment;
an engine disposed within the engine compartment;
at least one fire bottle configured to hold a fire extinguishing agent;
at least one agent tube coupled to the at least one fire bottle and configured to carry the fire extinguishing agent to the engine compartment; and
a nozzle on the at least one agent tube, the nozzle positioned above the engine and oriented in a downward-facing direction.

2. The rotorcraft of claim 1 , wherein the nozzle has one or more openings, and wherein the openings are facing downward.

3. The rotorcraft of claim 1 , further comprising:
at least one vertical firewall enclosing the engine compartment; and
wherein the at least one agent tube penetrates the at least one vertical firewall.

4. The rotorcraft of claim 1 , wherein the at least one fire bottle is located above the engine.

5. The rotorcraft of claim 1 , wherein the nozzle has at least one opening, and wherein the nozzle is configured so that gravity causes water or other liquid to drain out of the at least one opening instead of allowing the water or other liquid to flow into the at least one agent tube.

6. The rotorcraft of claim 1 , wherein the at least one agent tube extends from the at least one fire bottle at a downward slope from the least one fire bottle, preventing water or other liquid from entering the at least one agent tube.

7. The rotorcraft of claim 1 , wherein the at least one fire bottle comprises a squib cartridge and the at least one agent tube extending at a downward slope from the least one fire bottle preventing water or other liquid from entering the at least one agent tube prevents corroding the squib cartridge.

8. The rotorcraft of claim 1 , wherein the at least one agent tube extends downward from the at least one fire bottle and the at least one fire bottle comprises a squib cartridge and the at least one agent tube extending downward from the at least one fire bottle prevents water or other liquid from entering the at least one agent tube and corroding the squib cartridge.

9. A rotorcraft comprising:
an airframe having an engine compartment;
an engine disposed within the engine compartment;
at least one fire bottle located above the engine and configured to hold a fire extinguishing agent;
at least one agent tube coupled to the at least one fire bottle, extending downward from the at least one fire bottle, and configured to carry the fire extinguishing agent to the engine compartment; and
a nozzle on the at least one agent tube, the nozzle positioned below the least one fire bottle, above the engine and oriented in a downward-facing direction.

10. The rotorcraft of claim 9 , wherein the at least one fire bottle is located above the engine compartment.

11. The rotorcraft of claim 9 , wherein the at least one agent tube comprises at least two agent tubes extending along opposite sides of the engine, in the engine compartment.

12. The rotorcraft of claim 9 , wherein the at least one fire bottle comprises a squib cartridge and the at least one agent tube extending downward from the at least one fire bottle prevents water or other liquid from entering the at least one agent tube and corroding the squib cartridge.

13. The rotorcraft of claim 9 , further comprising:
at least one vertical firewall enclosing the engine compartment; and
wherein the at least one agent tube penetrates the at least one vertical firewall.

14. The rotorcraft of claim 9 , wherein the nozzle has at least one opening, and wherein the nozzle is configured so that gravity causes water or other liquid to drain out of the at least one opening instead of allowing the water or other liquid to flow into the at least one agent tube.

15. A rotorcraft comprising:
an airframe having an engine compartment;
an engine disposed within the engine compartment;
at least one fire bottle located beside the engine compartment and configured to hold a fire extinguishing agent;
at least one agent tube coupled to the at least one fire bottle, extending into the engine compartment generally in plane with a respective at least one of the at least one fire bottle, and configured to carry the fire extinguishing agent to the engine compartment; and
a nozzle on the at least one agent tube, the nozzle positioned above the engine and oriented in a downward-facing direction.

16. The rotorcraft of claim 15 , wherein the at least one agent tube extending generally in plane with a respective at least one of the at least one fire bottle further comprises the at least one agent tube extending at a downward slope from the least one fire bottle.

17. The rotorcraft of claim 16 wherein the at least one fire bottle comprises a squib cartridge and the at least one agent tube extending at a downward slope from the least one fire bottle prevents water or other liquid from entering the at least one agent tube and corroding the squib cartridge.

18. The rotorcraft of claim 15 , wherein the at least one fire bottle is located above the engine.

19. The rotorcraft of claim 15 , further comprising:
at least one vertical firewall enclosing the engine compartment; and
wherein the at least one agent tube penetrates the at least one vertical firewall.

20. The rotorcraft of claim 15 , wherein the nozzle has at least one opening, and wherein the nozzle is configured so that gravity causes water or other liquid to drain out of the at least one opening instead of allowing the water or other liquid to flow into the at least one agent tube.

Assignees

• Bell Textron Inc
• Textron Innovations Inc

Inventors

• Parsons Thomas Dewey
• Weaver Keith David
• Ludtke Chris James
• Madej Paul
• Birkenheuer Andrew Jordan

Classifications

• A62C3/08 Primary

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

• A62C31/02

  Nozzles specially adapted for fire-extinguishing · 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

• A62C35/68

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