Aircraft fuel tank inerting arrangement, method of inerting one or more aircraft fuel tanks, aircraft and software product

Patent metadata

Field	Value
Publication number	US-2016176535-A1
Application number	US-201514969183-A
Country	US
Kind code	A1
Filing date	Dec 15, 2015
Priority date	Dec 22, 2014
Publication date	Jun 23, 2016
Grant date	—

Abstract

A method is provided of inerting one or more fuel tanks of an aircraft. The method comprises: providing a temperature value indicative of a temperature at the aircraft's destination; comparing said temperature value with a predetermined value; and on the basis of said comparison, controlling the provision of inerting gas to the one or more aircraft fuel tanks. An aircraft fuel tank inerting arrangement, a software product and an aircraft are also provided.

First claim

1 . A method of inerting one or more fuel tanks of an aircraft, the method comprising:
providing a temperature value indicative of a temperature at the aircraft's destination; comparing said temperature value with a predetermined value; and on the basis of said comparison, controlling the provision of inerting gas to the one or more aircraft fuel tanks.

2 . A method according to claim 1 wherein the temperature value indicative of the temperature at the aircraft's destination is a static air temperature.

3 . A method according to claim 1 comprising requesting said temperature value from a source of information and receiving said temperature from said source of information.

4 . A method according to claim 3 wherein the source of information comprises a database comprising data providing relationships between temperature, a plurality of aircraft destinations, and optionally one or both of date and time of day.

5 . A method according to claim 1 wherein the temperature value indicative of the temperature at the aircraft's destination may is a predicted value.

6 . A method according to claim 1 wherein the temperature value is a measured value.

7 . A method according to claim 1 wherein the predetermined value to be compared with the indicative temperature is related to a property of the aircraft fuel.

8 . A method according to claim 7 wherein the predetermined value is related to a flammability limit of the aircraft's fuel.

9 . A method according to claim 1 wherein the comparison comprises calculating a difference between the predetermined value and the indicative temperature, wherein if the indicative temperature value is lower than the predetermined value by at least a certain margin, then this is indicative of there being no need for inerting gas.

10 . A method according to claim 1 wherein control of the provision of inerting gas is further dependent on one or more additional flight-related parameters.

11 . A method according to claim 10 wherein control of the provision of inerting gas is further dependent on one or more of the following parameters: aircraft altitude, aircraft attitude, time until next descent, time since last (i.e. immediately preceding) ascent, projected duration of next descent, amount of fuel in fuel tanks, gas pressure in fuel tanks, duration of previous (i.e. immediately preceding descent, oxygen content of gas (optionally in a fuel tank), nitrogen content of gas (optionally in a fuel tank), temperature indicative of fuel temperature, fuel temperature, external temperature and temperature of gas in fuel tank.

12 . A method according to claim 1 comprising controlling the provision of inerting gas further dependent on one or more of: a temperature indicative of fuel temperature; the time from the last ascent and the time to the next descent and the duration of the immediately-preceding descent and the time until the next descent.

13 . A method of inerting one or more fuel tanks of an aircraft, the method comprising:
requesting from a source of information a temperature value indicative of a temperature at the aircraft's destination; receiving from the source of information said temperature value indicative of a temperature at the aircraft's destination; comparing said temperature value with a predetermined value related to a property of the aircraft's fuel; and in response to the comparison between said temperature value and the predetermined value, controlling one or more valves and/or pumps arranged to control the supply of inerting gas to the one or more fuel tanks.

14 . A method according to claim 13 wherein the step of requesting from a source of information a temperature value indicative of the temperature at the aircraft's destination comprises transmitting a signal to a source of information remote from the aircraft, the signal requesting said temperature, and the step of receiving from the source of information said temperature value indicative of the temperature at the aircraft's destination comprises receiving a signal from a source of information remote from the aircraft.

15 . A method according to claim 13 wherein the step of requesting said temperature value from said source of information comprises transmitting instructions to interrogate a database comprising data providing relationships between temperature, a plurality of aircraft destinations, and optionally one or both of date and time of day and the step of receiving said temperature value from said source of information comprises receiving said temperature value from said database.

16 . A software product comprising a series of instructions arranged, when executed on a computer, to perform one or more of the steps of the method of claim 1 .

17 . An aircraft fuel tank inerting arrangement comprising;
a gas inlet; a gas separation unit in gaseous communication with the gas inlet and configured to remove oxygen from a flow of oxygen-containing gas to produce a flow of oxygen-depleted gas; at least one gas outlet configured to receive oxygen-depleted gas from the gas separation unit and to deliver oxygen-depleted gas to at least one aircraft fuel tank; a gas flow control module for controlling the flow of oxygen-depleted gas to at least one aircraft fuel tank; and a temperature input module for acquiring a temperature indicative of the temperature at the aircraft's destination; the gas flow control module being configured to receive an output from the temperature input module dependent on the temperature at the aircraft's destination and to control the flow of oxygen-depleted gas to the one or more fuel tanks in dependence on the output from the temperature input module.

18 . An aircraft fuel tank inerting arrangement according to claim 17 wherein the temperature input is configured to request a temperature value from a source of information and to receive a temperature value from the source of information.

9 . An aircraft comprising an aircraft fuel tank inerting arrangement according to claim 17 arranged to provide inerting gas to one or more fuel tanks of the aircraft.

Assignees

• Airbus Operations Ltd

Inventors

• Family Oliver
• Smiles Mark
• James Dylan

Classifications

• B64D43/00

  Arrangements or adaptations of instruments · CPC title

• A62C99/0018

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

• A62C3/08

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

• B64D37/32 Primary

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

• B64D2700/62447

  Operations & Transport · mapped topic