Aircraft fuel system

Patent metadata

Field	Value
Publication number	US-12486039-B2
Application number	US-202318316450-A
Country	US
Kind code	B2
Filing date	May 12, 2023
Priority date	Nov 29, 2022
Publication date	Dec 2, 2025
Grant date	Dec 2, 2025

Abstract

An aircraft fuel system includes a first fuel storage tank arranged to store a first fuel, a second fuel storage tank arranged to store a reduced oxygen fuel, and a fuel tank inerting system arranged to provide a reduced oxygen gas through a fuel contained within the second fuel storage tank to generate the reduced oxygen fuel within the second fuel storage tank. The fuel tank inerting system may include a fuel tank sparging system to inject the reduced oxygen gas directly into the fuel contained within the second fuel storage tank to generate the reduced oxygen fuel.

First claim

We claim:

1 . An aircraft propulsion system comprising:
at least one engine; and a fuel system including (a) a first fuel storage tank arranged to store a first fuel, (b) a second fuel storage tank arranged to store a reduced oxygen fuel, (c) a fuel tank inerting system arranged to provide a reduced oxygen gas through a fuel contained within the second fuel storage tank to generate the reduced oxygen fuel within the second fuel storage tank, and (d) a fuel oxygen reduction unit that generates a deoxygenated fuel from the first fuel stored in the first fuel storage tank and provides the deoxygenated fuel to the second fuel storage tank such that the fuel contained within the second fuel storage tank is the deoxygenated fuel, wherein the second fuel storage tank includes a fuel tank sparging system, the fuel tank sparging system being in airflow communication with the fuel tank inerting system and providing the reduced oxygen gas into the deoxygenated fuel within the second fuel storage tank to generate the reduced oxygen fuel.

2 . The aircraft propulsion system according to claim 1 , further comprising:
a first fuel supply line providing a flow of the first fuel from first fuel storage tank to the fuel oxygen reduction unit; a first gas return line providing a flow of a reduced oxygen gas from the fuel oxygen reduction unit to an ullage of the first fuel storage tank; and a second fuel supply line providing a flow of the deoxygenated fuel from the fuel oxygen reduction unit to the second fuel storage tank.

3 . An aircraft fuel system comprising:
a first fuel storage tank arranged to store a first fuel; a second fuel storage tank arranged to store a reduced oxygen fuel; a fuel tank inerting system arranged to provide a reduced oxygen gas through a fuel contained within the second fuel storage tank to generate the reduced oxygen fuel within the second fuel storage tank; and a fuel oxygen reduction unit that generates a deoxygenated fuel from the first fuel stored in the first fuel storage tank and provides the deoxygenated fuel to the second fuel storage tank such that the fuel contained within the second fuel storage tank is the deoxygenated fuel, wherein the second fuel storage tank includes a fuel tank sparging system, the fuel tank sparging system being in airflow communication with the fuel tank inerting system and providing the reduced oxygen gas into the deoxygenated fuel within the second fuel storage tank to generate the reduced oxygen fuel.

4 . The aircraft fuel system according to claim 3 , further comprising:
a first fuel supply line providing a flow of the first fuel from first fuel storage tank to the fuel oxygen reduction unit; and a second fuel supply line providing a flow of the deoxygenated fuel from the fuel oxygen reduction unit to the second fuel storage tank.

5 . The aircraft fuel system according to claim 4 , further comprising a first gas return line providing a flow of a reduced oxygen gas from the fuel oxygen reduction unit to an ullage of the first fuel storage tank.

6 . An aircraft fuel system comprising:
a first fuel storage tank arranged to store a first fuel; a second fuel storage tank arranged to store a reduced oxygen fuel; a fuel tank inerting system arranged to provide a reduced oxygen gas through a fuel contained within the second fuel storage tank to generate the reduced oxygen fuel within the second fuel storage tank; a first gas supply line providing a flow of oxygen rich gas from an ullage of the first fuel storage tank to the fuel tank inerting system, and a first gas return line providing a flow of the reduced oxygen gas from the fuel tank inerting system to the ullage of the first fuel storage tank; a second gas supply line providing a flow of oxygen rich gas from an ullage of the second fuel storage tank to the fuel tank inerting system, and a second gas return line providing a flow of the reduced oxygen gas from the fuel tank inerting system to the ullage of the second fuel storage tank; and a third gas return line providing a flow of the reduced oxygen gas from the fuel tank inerting system to a fuel tank sparging system in the second fuel storage tank, the fuel tank sparging system providing a flow of the reduced oxygen gas into the first fuel stored in the second fuel storage tank to generate the reduced oxygen fuel.

7 . The aircraft fuel system according to claim 6 , wherein the first fuel storage tank and the second fuel storage tank are separate portions of a same fuel tank.

8 . The aircraft fuel system according to claim 6 , further comprising a fault accommodation fuel supply line providing fluid communication from the first fuel storage tank to at least one engine.

9 . The aircraft fuel system according to claim 6 , further comprising a first fuel supply line providing fluid communication from the first fuel storage tank to the second fuel storage tank,
wherein the first fuel is provided from the first fuel storage tank to the second fuel storage tank via the first fuel supply line such that the fuel contained within the second fuel storage tank is the first fuel, and the reduced oxygen gas is provided to the first fuel contained within the second fuel storage tank to generate the oxygen reduced fuel.

10 . The aircraft fuel system according to claim 9 , wherein the fuel tank sparging system is in airflow communication with the fuel tank inerting system and provides the reduced oxygen gas into the first fuel within the second fuel storage tank.

11 . The aircraft fuel system according to claim 6 , further comprising an engine fuel supply line providing a flow of the reduced oxygen fuel from the second fuel storage tank to at least one engine.

12 . The aircraft fuel system according to claim 11 , further comprising a separator provided in the engine fuel supply line, the separator arranged to separate reduced oxygen gas from the reduced oxygen fuel flowing through the engine fuel supply line.

13 . An aircraft propulsion system comprising:
at least one engine; and a fuel system including (a) a first fuel storage tank arranged to store a first fuel, (b) a second fuel storage tank arranged to store a reduced oxygen fuel, (c) a fuel tank inerting system arranged to provide a reduced oxygen gas through a fuel contained within the second fuel storage tank to generate the reduced oxygen fuel within the second fuel storage tank, (d) a first gas supply line providing a flow of an oxygen rich gas from an ullage of the first fuel storage tank to the fuel tank inerting system, (e) a first gas return line providing a flow of the reduced oxygen gas from the fuel tank inerting system to the ullage of the first fuel storage tank, (f) a second gas supply line providing a flow of an oxygen rich gas from an ullage of the second fuel storage tank to the fuel tank inerting system, (g) a second gas return line providing a flow of the reduced oxygen gas from the fuel tank inerting system to the ullage of the second fuel storage tank, and (h) a third gas return line providing a flow of the reduced oxygen gas from the fuel tank inerting system to a fuel tank sparging system, the fuel tank sparging system providing a flow of the reduced oxygen gas into the first fuel stored in the second fuel storage tank to generate the reduced oxygen fuel.

14 . The aircraft propulsion system according to claim 13 , further comprising an engine fuel supply line providing a flow of the reduced oxygen fuel from the second fuel storage tank to the at least one engine.

15 . The aircraft propulsion system according to claim 13 , further comprising a first fuel supply l

Assignees

• Gen Electric

Inventors

• Murray Michael Joseph
• Moreno Patan Victor
• Miller Brandon W

Classifications

• F02C7/22

  Fuel supply systems · CPC title

• F23R3/28

  characterised by the fuel supply (burners F23D) · CPC title

• A62C3/08

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

• B01J19/14

  Production of inert gas mixtures; Use of inert gases in general · CPC title

• B01D53/00

  Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases, aerosols, (recovery of volatile solvents by condensation B01D5/00; sublimation B01D7/00; cold traps, cold baffles B01D8/00; working-up undefined gaseous mixtures obtained by cracking hydrocarbon oils C10G70/00; cleaning coal gas C10K; working-up of natural gas, or synthetic natural gas, C10L3/10; separation of difficult-to-condense gases or air by liquefaction F25J; for investigating materials G01N30/00) · CPC title