Aircraft fuel tank arrangement

Patent metadata

Field	Value
Publication number	US-9969501-B2
Application number	US-201414194596-A
Country	US
Kind code	B2
Filing date	Feb 28, 2014
Priority date	Feb 28, 2013
Publication date	May 15, 2018
Grant date	May 15, 2018

Abstract

An aircraft fuel tank arrangement for the relief of a pressure differential between the interior of the aircraft fuel tank and the ambient atmosphere is provided. The aircraft fuel tank arrangement comprises a removable cartridge received within a cartridge-receiving body located at least partially in the fuel tank, said cartridge comprising a first burstable member operable to rupture in the presence of a pressure differential between the interior of the aircraft fuel tank and the ambient atmosphere which is greater than a predetermined pressure differential.

First claim

The invention claimed is:

1. An aircraft fuel tank arrangement for the relief of a pressure differential between the interior of the aircraft fuel tank and the ambient atmosphere, the aircraft fuel tank arrangement comprising a removable cartridge received within a cartridge-receiving body located at least partially in the fuel tank, said cartridge comprising:
a first burstable member operable to rupture in the event that said pressure differential between the interior of the aircraft fuel tank and the ambient atmosphere is greater than a predetermined pressure differential;
a second burstable member operable to rupture in the event that said pressure differential is greater than a predetermined pressure differential, the predetermined pressure differential required to burst the second burstable member being different from the predetermined pressure differential required to burst the first burstable member;
the first and second burstable members being spaced apart, thereby defining a space therebetween, at least one fluid flow pathway being provided between the ambient atmosphere outside the aircraft fuel tank and the space between the first and second burstable members; and,
wherein the at least one fluid flow pathway is provided by one or more apertures provided in the second burstable member.

2. An aircraft fuel tank arrangement according to claim 1 wherein the first and second burstable members are spaced along a length of the cartridge.

3. An aircraft fuel tank arrangement according to claim 2 wherein the first burstable member is located inwardly of the second member.

4. An aircraft fuel tank arrangement according to claim 1 wherein the first burstable member is located at or proximate to a first end of the cartridge and the second burstable member is located at or proximate to a second end of the cartridge.

5. An aircraft fuel tank arrangement according to claim 4 wherein the first end of the cartridge is located in the interior of the fuel tank, and the second end is proximate to, or flush with, one or more adjacent surfaces.

6. An aircraft fuel tank arrangement according to claim 1 wherein the second burstable member is shaped so that water collecting on the second burstable member is directed to at least one of the apertures provided in the second burstable member.

7. An aircraft fuel tank arrangement according to claim 1 wherein the first and second burstable members are burst disks.

8. An aircraft fuel tank arrangement according to claim 1 comprising at least one fluid tight sealing member between the cartridge and the cartridge-receiving body.

9. An aircraft fuel tank arrangement according to claim 8 wherein one or more sealing members is provided at or proximate to a first end of the cartridge and one or more sealing members is provided at or proximate to a second end of the cartridge.

10. An aircraft fuel tank arrangement according to claim 1 wherein the cartridge comprises a cartridge body portion extending into the aircraft fuel tank.

11. An aircraft fuel tank arrangement according to claim 10 wherein the cartridge body portion is substantially cylindrical or frusto-conical.

12. An aircraft fuel tank arrangement according to claim 10 wherein the cartridge body portion defines a fluid pathway between the inside of the aircraft fuel tank and the ambient atmosphere outside the aircraft fuel tank in the event of operation of a sufficient pressure differential to rupture the first and second burstable members.

13. An aircraft fuel tank arrangement according to claim 10 wherein the cartridge body portion is tubular.

14. An aircraft fuel tank arrangement according to claim 10 wherein the first and second burstable members are attached to, and/or located within the cartridge body portion.

15. An aircraft fuel tank arrangement according to claim 1 , further comprising at least one continuous resistive or optically transmissive element for indicating whether the respective burstable member has been ruptured being attached to, or provided on, the first and/or second burstable member, the first and/or second burstable element which is provided with at least one continuous electrically-resistive or optically-transmissive element being operable to burst so as to make the at least one continuous electrically-resistive or optically-transmissive element discontinuous.

16. A cartridge for use in the aircraft fuel tank arrangement according to claim 1 .

17. A system for detecting the failure of a pressure-differential burstable member associated with an aircraft fuel tank, the system comprising:
(a) an aircraft fuel tank arrangement according to claim 15 ; and,
(b) an interrogating system operable to interrogate the electrical or optical characteristics of the one or more continuous electrically-resistive or optically-transmissive elements, and to produce an output indicative of the rupture status of said burstable member.

18. A system for controlling an event in response to the rupture of a pressure-differential rupture member associated with an aircraft fuel tank, the system comprising a failure detection system according to claim 17 , and a controller operable in response to the output from the interrogating system to control one or more aircraft functions dependent on the rupture status of the burstable member.

19. An aircraft fuel tank arrangement according to claim 1 , the cartridge being elongate.

20. An aircraft fuel tank arrangement for the relief of a pressure differential between the interior of the aircraft fuel tank and the ambient atmosphere, the aircraft fuel tank arrangement comprising a removable elongate tubular cartridge received within a cartridge-receiving body located at least partially in the fuel tank, said cartridge comprising:
a first burst disk operable to rupture in the event that said pressure differential between the interior of the aircraft fuel tank and the ambient atmosphere is greater than a predetermined pressure differential; and
the second burst disk being operable to rupture in the event that said pressure differential is greater than a predetermined pressure differential, the predetermined pressure differential required to burst the second burst disk being different from the predetermined pressure differential required to burst the first burst disk,
the first burst disk being located at, or proximate, to a first end of the cartridge and the second burst disk being located at, or proximate, to a second end of the cartridge, thereby providing a space between the first and second burst disks;
one or more apertures being provided in the second burst disk to provide at least one fluid flow pathway between the ambient atmosphere outside the aircraft fuel tank and the space between the first and second burst disk;
one or more sealing members being provided at, or proximate, to the first end of the cartridge between the cartridge and the cartridge-receiving body, and one or more sealing members being provided at, or proximate to, the second end of the cartridge between the cartridge and the cartridge-receiving body.

Assignees

• Airbus Operations Ltd

Inventors

• Haskins Richard
• Jones John

Classifications

• B64D37/04

  Arrangement thereof in or on aircraft · CPC title

• B64D37/32 Primary

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

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title