DEHUMIDIFICATION SYSTEM FOR USE IN A VEHICLE AND METHOD OF ASSEMBLING THEREOF

• US 20150210398A1
• Filed: 01/24/2014
• Published: 07/30/2015
• Est. Priority Date: 01/24/2014
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Vue, Fue Chue
• Granted Patent: US 9,988,151 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B23P 15/26 heat exchangers or the like making heat exchangers by methods covered by other subclasses B21D53/02
• CPC Class Codes: B64D 13/06 the air being conditioned pressurising B64D13/02
• CPC Class Codes: B64D 2013/0662 with humidity control
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency
• CPC Class Codes: Y10T 29/4935 Heat exchanger or boiler making

Abstract

A dehumidification system for use in a vehicle is provided. The system includes a thermally conductive member coupled to an outer skin of the vehicle, and a duct at least partially circumscribing the thermally conductive member such that an air flow passage is defined between the duct and the thermally conductive member. The thermally conductive member is configured to transmit a temperature of the outer skin to moisture-laden air channeled through the air flow passage.

Claims

1. A dehumidification system for use in a vehicle, said system comprising:

a thermally conductive member coupled to an outer skin of the vehicle; and

a duct at least partially circumscribing said thermally conductive member such that an air flow passage is defined between said duct and said thermally conductive member, said thermally conductive member configured to transmit a temperature of the outer skin to moisture-laden air channeled through said air flow passage.

2. The system in accordance with claim 1, wherein said thermally conductive member is configured to condense moisture from the moisture-laden air.

3. The system in accordance with claim 2, wherein said thermally conductive member comprises an outer surface configured to collect at least a portion of moisture condensed from the moisture-laden air.

4. The system in accordance with claim 2, wherein said thermally conductive member decreases to a first temperature that facilitates freezing the condensed moisture as the temperature of the outer skin decreases, and said thermally conductive member increases to a second temperature that facilitates melting the condensed moisture as the temperature of the outer skin increases.

5. The system in accordance with claim 1 further comprising a vacuum system coupled in flow communication with said duct and configured to create a negative pressure in said duct to draw the moisture-laden air through at least one air inlet opening defined in said duct.

6. The system in accordance with claim 1 further comprising a suction system coupled in flow communication with said duct and configured to drain fluid from said duct.

7. The system in accordance with claim 6, wherein said suction system comprises:

a sump coupled in flow communication with said duct; and

a ventilation system coupled in flow communication with said sump, wherein said suction system is configured to create a pressure in said sump that is lower than a pressure in said duct.

8. The system in accordance with claim 7, wherein said sump further comprises an outlet coupled in flow communication with a bilge.

9. An aircraft assembly comprising:

a fuselage comprising an outer skin; and

a dehumidification system comprising;

a thermally conductive member coupled to said outer skin of said fuselage; and

a duct at least partially circumscribing said thermally conductive member such that an air flow passage is defined between said duct and said thermally conductive member, wherein said thermally conductive member is configured to transmit a temperature of the outer skin to moisture-laden air channeled through said air flow passage.

10. The assembly in accordance with claim 9, wherein said fuselage further comprises a crown configured to receive moisture-laden air therein, said duct oriented such that at least one air inlet opening defined therein is coupled in flow communication with said crown.

11. The assembly in accordance with claim 9, wherein said thermally conductive member is configured to condense moisture from the moisture-laden air.

12. The assembly in accordance with claim 11, wherein said thermally conductive member comprises an outer surface configured to collect at least a portion of moisture condensed from the moisture-laden air.

13. The assembly in accordance with claim 11, wherein said thermally conductive member decreases to a first temperature that facilitates freezing the condensed moisture as the temperature of the outer skin decreases, and said thermally conductive member increases to a second temperature that facilitates melting the condensed moisture as the temperature of the outer skin increases.

14. The assembly in accordance with claim 9 further comprising a vacuum system coupled in flow communication with said duct and configured create a negative pressure in said duct to draw the moisture-laden air through at least one air inlet opening defined in said duct.

15. A method of assembling a dehumidification system for use in an aircraft assembly, said method comprising:

coupling a thermally conductive member to an outer skin of the aircraft assembly; and

at least partially circumscribing the thermally conductive member with a duct such that an air flow passage is defined between the duct and the thermally conductive member, wherein the thermally conductive member is configured to transmit a temperature of the outer skin to moisture-laden air channeled through the air flow passage.

16. The method in accordance with claim 15 further comprising extending at least one of the thermally conductive member and the duct along a length of a fuselage of the aircraft assembly.

17. The method in accordance with claim 15, wherein coupling a thermally conductive member comprises:

coupling a first portion of the thermally conductive member to an inner surface of the outer skin; and

extending a second portion of the thermally conductive member at least partially into a crown of the aircraft assembly.

18. The method in accordance with claim 15 further comprising orienting the duct such that at least one air inlet opening defined therein is coupled in flow communication with a crown of the aircraft assembly.

19. The method in accordance with claim 18 further comprising coupling a vacuum system in flow communication with the duct, wherein the vacuum system is configured create a negative pressure in the duct to draw the moisture-laden air through the at least one air inlet opening.

20. The method in accordance with claim 15 further comprising coupling a suction system in flow communication with the duct, wherein the suction system is configured to create a negative pressure in the duct to drain fluid from the duct.