Halon alternatives for aircraft fire suppression

Patent metadata

Field	Value
Publication number	US-2024033553-A1
Application number	US-202217876059-A
Country	US
Kind code	A1
Filing date	Jul 28, 2022
Priority date	Jul 28, 2022
Publication date	Feb 1, 2024
Grant date	—

Abstract

Fire suppression systems for aircraft include an air source, a first ASM configured to generate inert gas from air from the air source and supply inert gas to a fuel tank, and a second ASM configured to generate inert gas from the air from the air source and supply inert gas to a protected space of the aircraft. The second ASM comprises a membrane having inherent microporosity. A controller, in operable communication with the ASMs, is configured to operate the first ASM and not the second ASM during a first state of operation, and in response to a fire detected in the protected space, operate the second ASM to supply an inert gas from the second ASM to the protected space in a second state of operation.

First claim

What is claimed is:

1 . A fire suppression system for an aircraft, the fire suppression system comprising:
a pressurized air source; a first air separation module configured to receive pressurized air from the pressurized air source, the first air separation module arranged to generate inert gas from the received pressurized air and supply the generated inert gas to a fuel tank of the aircraft; a second air separation module configured to receive pressurized air from the pressurized air source, the second air separation module arranged to generate inert gas from the received pressurize air and supply the generated inert gas to a protected space of the aircraft, wherein the second air separation module comprises a membrane having inherent microporosity; and a controller in operable communication with each of the first air separation module and the second air separation module, the controller configured to:
direct the pressurized air to the first air separation module and direct no pressurized air to the second air separation module during a first state of operation, and
in response to a fire detected in the protected space, direct at least a portion of the pressurized air to the second air separation module and supply an inert gas from the second air separation module to the protected space in a second state of operation.

2 . The fire suppression system of claim 1 , wherein the first air separation module comprises at least one of a polyimide membrane, a polysulfone membrane, or a poly-phenylene membrane.

3 . The fire suppression system of claim 1 , wherein the controller is configured to control a first valve configured to control flow of pressurized air to the first air separation module and a second valve configured to control flow of pressurized air to the second air separation module.

4 . The fire suppression system of claim 1 , wherein the second state of operation is a low rate discharge fire suppression operation.

5 . The fire suppression system of claim 1 , further comprising a product gas cooler arranged between the second air separation module and the protected space.

6 . The fire suppression system of claim 1 , further comprising a cooling heat exchanger arranged between the pressurized air source and the first air separation module.

7 . The fire suppression system of claim 6 , wherein the second air separation module is arranged upstream from the cooling heat exchanger.

8 . The fire suppression system of claim 6 , wherein the second air separation module is arranged downstream from the cooling heat exchanger.

9 . The fire suppression system of claim 1 , wherein the pressurized air source is a portion of an engine of the aircraft, the system comprising a precooler arranged between the pressurized air source and each of the first air separation module and the second air separation module.

10 . The fire suppression system of claim 1 , wherein the membrane having inherent microporosity has at least one of (i) an oxygen permeance of 100 GPU or greater or (ii) a selectivity ratio of 6 or greater.

11 . The fire suppression system of claim 1 , wherein the membrane having inherent microporosity comprises a membrane formed from Thermally Rearranged polymers.

12 . The fire suppression system of claim 1 , wherein the membrane having inherent microporosity comprises a membrane formed from Polymers of Intrinsic Microporosity.

13 . The fire suppression system of claim 1 , wherein, in the second state of operation, the controller is configured to direct a portion of the pressurized air to the first air separation module and a portion of the pressurized air to the second air separation module.

14 . The fire suppression system of claim 13 , wherein an inert gas generated by the first air separation module is mixed with an inert gas generated by the second air separation module prior to being supplied to the protected space.

15 . The fire suppression system of claim 1 , further comprising a high rate discharge system comprising Halon to be dispensed into the protected space in response to the fire detection.

16 . The fire suppression system of claim 15 , wherein after performing a high rate discharge operation using the high rate discharge system, the second air separation module is controlled to direct inert gas to the protected space in a low rate discharge operation.

17 . The fire suppression system of claim 1 , wherein the inert gas generated by the second air separation module has an oxygen content of 15% or less.

18 . A method of supplying inerting gas to a fire-protected space of an aircraft for fire suppression, the method comprising:
extracting pressurized air from a pressurized air source; directing the pressurized air to a first air separation module configured generate inert gas and supply the generated inert gas to a fuel tank of the aircraft during a first state of operation; and in response to a fire detected in a protected space of the aircraft, directing at least a portion of the pressurized air to a second air separation module and supplying an inert gas from the second air separation module to the protected space in a second state of operation, wherein the second air separation module comprises a membrane having inherent microporosity.

19 . The method of claim 18 , wherein, in the second state of operation, the method comprises directing a portion of the pressurized air to the first air separation module and a portion of the pressurized air to the second air separation module.

20 . The method of claim 18 , further comprising performing a high rate discharge operation in response to the detected fire prior to operating the second air separation module.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Cordatos Haralambos
• Rheaume Jonathan

Classifications

• A62C99/0018 Primary

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

• A62C3/08 Primary

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

• B01D53/226

  in serial connexion · CPC title

• B01D53/228

  characterised by specific membranes · CPC title

• B01D71/64

  Polyimides; Polyamide-imides; Polyester-imides; Polyamide acids or similar polyimide precursors · CPC title