Aircraft fuel tank inerting system

Patent metadata

Field	Value
Publication number	US-9833738-B2
Application number	US-201514830989-A
Country	US
Kind code	B2
Filing date	Aug 20, 2015
Priority date	Aug 22, 2014
Publication date	Dec 5, 2017
Grant date	Dec 5, 2017

Abstract

A method of generating oxygen depleted air on an aircraft, and an aircraft fuel tank inerting system. The method including the steps of passing a first proportion of air through an air pressure reduction device to produce a supply of reduced pressure air, passing a second proportion along one side of a membrane of an air separation module, exposing the other side of the membrane of the air separation module to the reduced pressure air, so that oxygen is extracted from the second proportion of air across the membrane and the air separation module exhausts oxygen depleted air for inerting an aircraft fuel tank.

First claim

The invention claimed is:

1. A method of generating oxygen depleted air on an aircraft comprising the steps of: taking air from a source, wherein the air source is a ram air inlet, such that, in use, atmospheric air collected from the ram air inlet is supplied to both sides of the air separation module;
passing a first proportion of the atmospheric air through an air pressure reduction device to produce a supply of reduced pressure atmospheric air; passing a second proportion of the atmospheric air through a filter to produce a filtered atmospheric air supply, the first proportion of atmospheric air bypassing the filter; passing the filtered atmospheric air along one side of a membrane of an air separation module, so that a filtered air supply is passed along one side of the membrane of the air separation module; exposing the other side of the membrane of the air separation module to the reduced pressure atmospheric air, so that oxygen passes from the filtered atmospheric air on said one side of the membrane to the reduced pressure atmospheric air on said other side of the membrane, exhausting the filtered atmospheric air from the air separation module as filtered oxygen depleted atmospheric air; and
passing the filtered oxygen depleted atmospheric air exhausted from the air separation module to a fuel tank on the aircraft for inerting the fuel tank.

2. A method of generating oxygen depleted air on an aircraft according to claim 1 wherein the air pressure reduction device comprises a vacuum generator, whereby the first proportion of air is passed through a constriction to produce the reduced pressure air supply.

3. An aircraft fuel tank inerting system comprising:
a ram air inlet,
an air pressure reduction device,
an air separation module, the air separation module having first and second sides separated by a membrane, wherein in use, the first side of the air separation module is supplied with a proportion of the atmospheric air from the ram air inlet, the second side of the air separation module is exposed to a reduced pressure atmospheric air supply from the air pressure reduction device, so that oxygen passes across the membrane from the first side to the second side of the air separation module and the first side of the air separation module exhausts oxygen depleted atmospheric air, with an outlet configured to pass the oxygen depleted atmospheric air to an aircraft fuel tank for inerting the fuel tank, and
a filter arranged between the ram air inlet and the air separation module, wherein in use, the proportion of the atmospheric air supplied to the first side of the air separation module is passed through the filter, and a proportion of atmospheric air supplied to the air pressure reduction device bypasses the filter.

4. An aircraft fuel tank inerting system according to claim 3 , wherein the ram air inlet is in the form of a NACA duct.

5. An aircraft fuel tank inerting system according to claim 3 additionally comprising a compressor, the compressor being arranged between the air source and the air separation module.

6. An aircraft fuel tank inerting system according to claim 3 wherein the air pressure reduction device comprises a vacuum generator.

7. An aircraft fuel tank inerting system according to claim 6 , wherein the vacuum generator is venturi based.

8. An aircraft fuel tank inerting system according to claim 3 , where the air separation module comprises a bundle of hollow fibres, the channel of the hollow fibres defining the first side of the air separation module.

9. An aircraft incorporating the aircraft fuel tank inerting system according to claim 3 .

Assignees

• Airbus Operations Ltd

Inventors

• Burnell Stephen
• Leigh Tim

Classifications

• B01D2053/224

  with hollow fibres · CPC title

• Y02T50/44

  Cross-Sectional Technologies · mapped topic

• B01D53/22 Primary

  by diffusion (manufacturing semi-permeable membranes B01D67/00; form, structure or properties of semi-permeable membranes B01D69/00; material for semi-permeable membranes B01D71/00) · CPC title

• B01D2257/104

  Oxygen · CPC title

• B01D2258/06

  Polluted air · CPC title