AIRCRAFT FUEL TANK VENTILATION

• US 20120103192A1
• Filed: 07/09/2010
• Published: 05/03/2012
• Est. Priority Date: 07/22/2009
• Status: Active Grant

• Current Assignee: Airbus Operations Limited (Airbus SE)
• Original Assignee: Airbus Operations Limited (Airbus SE)
• Inventors: Lam, Joseph K-W, Parmenter, David, Masters, Simon
• Granted Patent: US 8,753,429 B2
• Time in Patent Office: Days
• US Class Current: 95/91
• CPC Class Codes: B64D 37/10 to facilitate fuel pressurisation
• CPC Class Codes: B64D 37/32 Safety measures not otherwise provided for, e.g. preventing explosive conditions extinguishing or preventing fires in aircraft A62C
• CPC Class Codes: B64D 37/34 Conditioning fuel, e.g. heating during filling B64D37/18
• CPC Class Codes: Y10T 137/86324 Tank with gas vent and inlet or outlet

Abstract

An aircraft fuel tank ventilation system includes a dehumidifying device disposed in flow communication between a vent open to the atmosphere and a fuel tank. A method of dehumidifying air introduced into an aircraft fuel tank via a ventilation system includes directing atmospheric air through a dehumidifying device disposed in flow communication between a vent of the ventilation system and the fuel tank, which removes water vapour from the air flowing from the vent towards the fuel tank. A method of regenerating a desiccant medium used to dehumidify air introduced into an aircraft fuel tank via a ventilation system includes directing air through the desiccant medium so as to dry the desiccant medium.

Claims

1. An aircraft fuel tank ventilation system, comprising a dehumidifying device disposed in flow communication between a vent open to the ambient atmosphere and a fuel tank, wherein the dehumidifying device includes a desiccant medium for removing water vapour from ambient air flowing from the vent towards the fuel tank, and the ventilation system further comprising a valve for directing a flow of air through the dehumidifying device for regenerating the desiccant medium, and an outlet for discharging the regenerative air that has passed through the desiccant medium to the ambient atmosphere.

2. A ventilation system according to claim 1, wherein the valve is selectively openable and in its open position also provides the outlet, and the outlet is positioned aft of the vent such that forward movement of the aircraft creates a pressure differential between the vent and the outlet to drive the flow of regenerative air through the dehumidifying device.

3. A ventilation system according to claim 2, wherein the dehumidifying device includes a heating element for heating the desiccant medium.

4. A ventilation system according to claim 2, further comprising a hot air outlet disposed adjacent the desiccant medium.

5. A ventilation system according to claim 1, wherein the vent also provides the outlet, and the valve is operatively connected to a hot air outlet for delivering a supply of hot regenerative air through the dehumidifying device.

6. A ventilation system according to claim 5, wherein the hot air outlet is disposed adjacent the desiccant medium.

7. A ventilation system according to claim 1, further comprising a bypass of the dehumidifying device in flow communication between the vent and the fuel tank.

8. A ventilation system according to claim 7, wherein the bypass includes a valve.

9. A ventilation system according to claim 1, wherein the dehumidifying device is disposed in flow connection between the vent and a vent tank.

10. A method of regenerating a desiccant medium of a dehumidifying device in an aircraft fuel tank ventilation system, wherein the dehumidifying device is disposed in flow communication between a vent open to the ambient atmosphere and a fuel tank, and the desiccant medium is adapted to remove water vapour from ambient air flowing from the vent towards the fuel tank, the method comprising directing a flow of air through the dehumidifying device for regenerating the desiccant medium, and discharging the regenerative air that has passed through the desiccant medium to the ambient atmosphere.

11. A method according to claim 10, wherein the outlet is positioned aft of the vent, and forward movement of the aircraft causes a pressure differential between the vent and the outlet to drive the flow of regenerative air through the dehumidifying device.

12. A method according to claim 11, further comprising heating the desiccant medium.

13. A method according to claim 11, further comprising directing a supply of hot air towards the desiccant medium.

14. A method according to claim 10, wherein the vent also provides the outlet, and the method further comprises delivering a supply of hot air through the dehumidifying device.

15. A method according to claim 10, wherein the method is operated during the cruise phase of an aircraft flight.