Aircraft fuel tank system

Patent metadata

Field	Value
Publication number	US-9475383-B2
Application number	US-86902810-A
Country	US
Kind code	B2
Filing date	Aug 26, 2010
Priority date	Sep 4, 2009
Publication date	Oct 25, 2016
Grant date	Oct 25, 2016

Abstract

An aircraft fuel tank system is disclosed in which a vent tank is provided with an additional ullage vent for use, in combination with an eternal flamer barrier means, when refueling.

First claim

The invention claimed is:

1. An aircraft fuel tank system, comprising:
one or more aircraft fuel tanks holding and supplying aircraft fuel to aircraft engines within said aircraft;
an aircraft surge tank comprising an inlet from said one or more aircraft fuel tanks and a first ullage vent opening and a second ullage vent opening, said aircraft surge tank being arranged to provide a predetermined maximum fuel capacity and having a minimal ullage at said maximum fuel capacity;
a first vent pipe having a first open end in fluid communication with said first ullage vent opening and a second open end positioned within said minimal ullage of said surge tank, said first vent pipe being arranged to provide fluid communication between said minimal ullage and said first ullage vent opening;
a second vent pipe having a first open end in fluid communication with said second ullage vent opening and a second open end positioned within said minimal ullage of said surge tank, said second vent pipe being arranged to provide fluid communication between said minimal ullage and said second ullage vent opening; and
a coupling mechanism sealingly externally coupling an external flame barrier to said second ullage vent opening so as to provide fluid communication between said second vent pipe and atmosphere via the coupled external flame barrier, and wherein said external flame barrier is permanently open to fluid flow.

2. An aircraft fuel tank system according to claim 1 in which said coupling is arranged for the removable coupling of the external flame barrier.

3. An aircraft fuel tank system according to claim 1 in which said second ullage vent opening is provided with a closure operable to seal said second ullage vent.

4. An aircraft fuel tank system according to claim 3 in which said closure is arranged to open in response to the engagement of an external flame barrier with said coupling mechanism.

5. An aircraft fuel tank system according to claim 1 in which said second open end of said second vent pipe is positioned at a higher level in said minimal ullage that said second open end of said first vent pipe.

6. An aircraft fuel tank system according to claim 1 in which said second vent pipe is positioned inboard of said first vent pipe.

7. An aircraft fuel tank system according to claim 1 in which said first vent pipe comprises an internal flame barrier.

8. An aircraft fuel tank system according to claim 1 in which said first vent pipe comprises an ice screen.

9. An aircraft fuel tank system according to claim 1 in which said second ullage vent opening is provided within said minimal ullage of said surge tank when said aircraft is level and said second vent pipe is omitted.

10. An aircraft fuel tank system according to claim 9 in which said second ullage vent is positioned in the highest point in said minimal ullage when said aircraft is level.

11. An aircraft fuel tank system, comprising:
a surge tank comprising an inlet from one or more fuel tanks and a first and second ullage vent means, said surge tank being arranged to provide a predetermined maximum fuel capacity and having a minimal ullage at said maximum fuel capacity;
a first vent pipe having a first open end in fluid communication with said first ullage vent means and a second open end positioned within said minimal ullage of said surge tank, said first vent pipe being arranged to provide fluid communication between said minimal ullage and said first ullage vent means;
a second vent pipe having a first open end in fluid communication with said second ullage vent means and a second open end positioned within said minimal ullage of said surge tank, said second vent pipe being arranged to provide fluid communication between said minimal ullage and said second ullage vent means; and
coupling means arranged for sealingly externally coupling an external flame barrier means to said second ullage vent means so as to provide fluid communication between said second vent pipe and atmosphere via a coupled external flame barrier means, wherein said external flame barrier means is formed from a layered wire mesh material.

12. An aircraft fuel tank system, comprising:
a surge tank comprising an inlet from one or more fuel tanks and a first and second ullage vent means, said surge tank being arranged to provide a predetermined maximum fuel capacity and having a minimal ullage at said maximum fuel capacity;
a first vent pipe having a first open end in fluid communication with said first ullage vent means and a second open end positioned within said minimal ullage of said surge tank, said first vent pipe being arranged to provide fluid communication between said minimal ullage and said first ullage vent means;
a second vent pipe having a first open end in fluid communication with said second ullage vent means and a second open end positioned within said minimal ullage of said surge tank, said second vent pipe being arranged to provide fluid communication between said minimal ullage and said second ullage vent means; and
coupling means arranged for sealingly externally coupling an external flame barrier means to said second ullage vent means so as to provide fluid communication between said second vent pipe and atmosphere via a coupled external flame barrier means, wherein said external flame barrier means is formed from a non-woven mesh material.

Assignees

• Lynas Christopher
• James Peter William
• Airbus Operations Ltd

Inventors

• Lynas Christopher
• James Peter William

Classifications

• B64D2700/62447

  Operations & Transport · mapped topic

• B64D37/10 Primary

  to facilitate fuel pressurisation · CPC title

• B60K15/035 Primary

  characterised by venting means · CPC title

• B64D37/32

  Safety measures not otherwise provided for, e.g. preventing explosive conditions · CPC title