Aircraft fuel tank flammability reduction methods and systems

Patent metadata

Field	Value
Publication number	US-9327243-B2
Application number	US-201414477058-A
Country	US
Kind code	B2
Filing date	Sep 4, 2014
Priority date	Aug 24, 2012
Publication date	May 3, 2016
Grant date	May 3, 2016

Abstract

An aircraft fuel tank flammability reduction method includes feeding pressurized air into an air separation module containing an oxygen separation membrane. The method includes contacting the separation membrane with the air feed, permeating oxygen from the air feed through the separation membrane, and producing nitrogen-enriched air from the air separation module as a result of removing oxygen from the air feed. The NEA from the air separation module is substantially cooled in a NEA flow heat exchanger and the substantially cooled, nitrogen-enriched air is fed into the fuel tank on board the aircraft. An aircraft fuel tank flammability reduction system includes a NEA flow heat exchanger configured to cool substantially the nitrogen-enriched air from the air separation module and a fuel tank on board the aircraft configured to receive the cooled nitrogen-enriched air.

First claim

What is claimed is:

1. An aircraft fuel tank flammability reduction method comprising:
feeding pressurized air into an air separation module containing an oxygen separation membrane;
contacting the separation membrane with the air feed, permeating oxygen from the air feed through the separation membrane, and producing nitrogen-enriched air from the air separation module as a result of removing oxygen from the air feed;
substantially cooling the nitrogen-enriched air (NEA) from the air separation module in a NEA flow heat exchanger downstream of the air separation module; and
feeding the substantially cooled, nitrogen-enriched air into the fuel tank on board the aircraft.

2. The method of claim 1 wherein the separation membrane comprises a hollow fiber membrane and the air feed exhibits a normal operating temperature of at least 100° C. (212° F.).

3. The method of claim 1 further comprising a feed flow heat exchanger receiving the pressurized air from a source for the pressurized air and substantially cooling the air feed upstream from the air separation module.

4. The method of claim 3 further comprising directing a same cooling flow to the NEA flow heat exchanger and the feed flow heat exchanger.

5. The method of claim 4 wherein the cooling flow comprises ram air.

6. The method of claim 4 wherein the NEA flow heat exchanger receives the cooling flow upstream from the feed flow heat exchanger.

7. The method of claim 4 wherein the NEA flow heat exchanger receives the cooling flow downstream from the feed flow heat exchanger.

8. The method of claim 4 wherein the NEA flow heat exchanger receives the cooling flow in parallel with the feed flow heat exchanger.

9. The method of claim 4 wherein the NEA flow heat exchanger comprises an inner duct inside an outer duct, the method comprising flowing the nitrogen-enriched air through the inner duct and flowing the cooling flow of the NEA flow heat exchanger between the inner duct and the outer duct.

10. The method of claim 9 wherein the cooling flow of the NEA flow heat exchanger between the inner duct and the outer duct comprises the cooling flow to the feed flow heat exchanger.

11. The method of claim 1 further comprising feeding the pressurized air from a source for the pressurized air into the air separation module without substantially cooling the air feed in a heat exchanger.

12. The method of claim 1 wherein the NEA flow heat exchanger receives a cooling flow selected from among ram air, cabin air, cargo compartment air, ambient air, a cooling flow cooled by a skin heat exchanger, and a cooling flow cooled by an environmental control system.

13. The method of claim 1 wherein substantially cooling the NEA comprises passive, convective cooling by the NEA flow heat exchanger in a compartment containing the air separation module.

14. An aircraft fuel tank flammability reduction system comprising:
a source configured to produce pressurized air;
an air separation module configured to receive air feed from the pressurized air source;
an oxygen separation membrane in the air separation module configured to permeate oxygen from the air feed through the separation membrane and to produce nitrogen-enriched air (NEA) from the air separation module as a result of removing oxygen from the air feed;
a NEA flow heat exchanger downstream of the air separation module and configured to substantially cool the nitrogen-enriched air from the air separation module; and
a fuel tank on board the aircraft configured to receive the cooled nitrogen-enriched air.

15. The system of claim 14 wherein the separation membrane comprises a hollow fiber membrane and is configured to permeate oxygen at a normal operating temperature of at least 100° C. (212° F.).

16. The system of claim 14 further comprising a feed flow heat exchanger configured to receive the pressurized air from the source for the pressurized air and to substantially cool the air feed upstream from the air separation module.

17. The system of claim 16 wherein the system is configured to direct a same cooling flow to the NEA flow heat exchanger and the feed flow heat exchanger.

18. The system of claim 17 wherein the system is configured to provide ram air as the cooling flow.

19. The system of claim 17 wherein the NEA flow heat exchanger is configured to receive the cooling flow upstream from the feed flow heat exchanger.

20. The system of claim 17 wherein the NEA flow heat exchanger comprises an inner duct inside an outer duct, the system being configured to flow the nitrogen-enriched air through the inner duct and to flow the cooling flow of the NEA flow heat exchanger between the inner duct and the outer duct.

Assignees

• Boeing Co

Inventors

• Jojic Ivana
• Snow Jr Donald R
• Grim Alan
• Hart Colin W

Classifications

• B01D2053/224

  with hollow fibres · CPC title

• B01D53/228

  characterised by specific membranes · CPC title

• B01D2257/104

  Oxygen · CPC title

• B01D2311/106

  Cooling · CPC title

• B01D63/02 Primary

  Hollow fibre modules · CPC title