Method and system for inerting a fuel tank

Patent metadata

Field	Value
Publication number	US-10758760-B2
Application number	US-201715654241-A
Country	US
Kind code	B2
Filing date	Jul 19, 2017
Priority date	Aug 3, 2016
Publication date	Sep 1, 2020
Grant date	Sep 1, 2020

Abstract

A method for the inerting of at least one fuel tank of an aircraft, by means of at least one inert gas generation system, remarkable in that the inert gas generation system is started when at least one oxygen sensor within the tank measures an oxygen level that is above a high threshold.

First claim

The invention claimed is:

1. A method for inerting at least one fuel tank of an aircraft, by means of at least one inert gas generation system, comprising: measuring an oxygen level and comparing said oxygen level to a high threshold and a low threshold, wherein the at least one inert gas generation system is turned on and injects inert gas into the at least one fuel tank when at least one oxygen sensor within the tank measures an oxygen level that is above said high threshold value, and the at least one inert gas generation system is turned off when the measured oxygen level is below said low threshold value.

2. The method according to claim 1 , wherein the high threshold value is 10% oxygen.

3. The method according to claim 1 , wherein the low threshold value is 8% oxygen.

4. The method according to claim 1 , wherein the at least one inert gas generation system is turned on when a means of information regarding a flight of the aircraft indicate a determined number of minutes before a beginning of a descent phase of the aircraft.

5. A system for the inerting of at least one fuel tank of an aircraft, said system including at least one inert gas generation system supplied with air, means for the distribution and injection of an inert gas into the at least one fuel tank connected to the at least one inert gas generation system, and at least one oxygen sensor installed within the at least one fuel tank, wherein the system for the inerting includes a management unit connected to the at least one oxygen sensor and to the at least one inert gas generation system, that is programmed to register measurements from the at least one oxygen sensor in real time, and to turn on the at least one inert gas generation system and to inject the inert gas into the fuel tank when an oxygen level measurement is above a high threshold value and the management unit is programmed to turn off the at least one inert gas generation system when the oxygen level measurement is below a low threshold value.

6. The system according to claim 5 , wherein the high threshold value is 10% oxygen.

7. The system according to claim 5 , wherein the low threshold value is 8% oxygen.

8. The system according to claim 5 , wherein the management unit is programmed to register, in real time, information regarding a mission of the aircraft and to turn on the at least one inert gas generation system when the registered information indicates a duration before a beginning of a descent phase of the aircraft of less than 70 minutes.

9. A method for inerting at least one fuel tank of an aircraft, by at least one inert gas generation system comprising:
turning on the at least one inert gas generation system and injecting inert gas into the at least one fuel tank when at least one oxygen sensor within the at least one tank measures an oxygen level that is above a high threshold value; and
turning off the at least one inert gas generation system when a measured oxygen level is below a low threshold value.

10. The method according to claim 9 , wherein the high threshold value is 10% oxygen.

11. The method according to claim 9 , wherein the low threshold value is 8% oxygen.

12. The method according to claim 9 , wherein the at least one inert gas generation system is turned on when information regarding the flight of the aircraft as provided by a management unit which comprises an electronic board including software that is connected to an aircraft computer indicates a determined number of minutes before a beginning of a descent phase of the aircraft.

Assignees

• Zodiac Aerotechnics

Inventors

• Giroud Nelly
• Reynard Bruno
• Vandroux Olivier
• Mysliwiec Emilie

Classifications

• B64D37/32

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

• B64D37/02

  Tanks (tanks constructed integrally with aircraft wings B64C3/34) · CPC title

• A62C3/08 Primary

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

• A62B7/14

  for high-altitude aircraft · CPC title

• A62C99/0018 Primary

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