Water supply system for use in an aircraft and a method for preventing freezing of water lines
A water supply system for use in an aircraft, and a method for preventing blockages in a water supply system in an aircraft. The system comprises a central water tank comprising a fluid inlet and a fluid outlet, a supply conduit for permitting fluid flow from the outlet of the central water tank to a user equipment. At least a section of the supply conduit is connected and thermally coupled to an aircraft air duct so as to enable a transfer of thermal energy to the supply conduit therefrom to maintain the temperature of the water in the supply conduit above the freezing temperature thereof.
1 . A water supply system for use in an aircraft, the water supply system comprising:
a central water tank comprising a fluid inlet and a fluid outlet;
a supply conduit configured to permit fluid flow from the fluid outlet of the central water tank to a user equipment;
wherein at least a section of the supply conduit is connected and thermally coupled to an aircraft auxiliary conduit so as to enable a transfer of thermal energy to the supply conduit therefrom to maintain a temperature of water in the supply conduit above a freezing temperature thereof; and
wherein the supply conduit is disposed within an enclosure, the enclosure coupled to the aircraft auxiliary conduit.
2 . The water supply system of claim 1 , wherein the aircraft auxiliary conduit is an air duct.
3 . The water supply system of claim 1 , wherein the supply conduit extends along an axial direction of the aircraft auxiliary conduit.
4 . The water supply system of claim 1 , wherein the enclosure is an elongate enclosure configured to extend along an axial direction of the aircraft auxiliary conduit.
5 . The water supply system of claim 1 , wherein the enclosure is directly coupled to an external surface of the aircraft auxiliary conduit.
6 . The water supply system of claim 1 , wherein the enclosure comprises a cover located radially outwardly of the supply conduit, the cover comprising a thermal insulator.
7 . The water supply system of claim 1 , wherein the supply conduit is disposed between the aircraft auxiliary conduit and a thermal insulator extending circumferentially around the aircraft auxiliary conduit.
8 . The water supply system of claim 1 , wherein the supply conduit is disposed in a discontinuity of a thermal insulator extending circumferentially discontinuously around the aircraft auxiliary conduit.
9 . The water supply system of claim 1 , wherein the supply conduit is located externally of a thermal insulator extending circumferentially around the aircraft auxiliary conduit.
10 . The water supply system of claim 1 , wherein a diameter of the supply conduit is smaller than a diameter of the aircraft auxiliary conduit.
11 . The water supply system of claim 1 , wherein the aircraft auxiliary conduit has an internal temperature of above 10 degrees Celsius.
12 . The water supply system of claim 1 , comprising a plurality of supply conduits coupled to the aircraft auxiliary conduit.
13 . A method for preventing freezing or icing in a water supply system in an aircraft, comprising:
providing a supply conduit for permitting fluid flow from an outlet of a central water tank to a user equipment;
thermally coupling the supply conduit to an aircraft auxiliary conduit so as to enable a transfer of thermal energy to the supply conduit therefrom;
providing thermal energy to the supply conduit from the aircraft auxiliary conduit so as to maintain a temperature of water in the supply conduit above a freezing temperature thereof; and
wherein the supply conduit is disposed within an enclosure, the enclosure coupled to the aircraft auxiliary conduit.
14 . The method of claim 13 , wherein the aircraft auxiliary conduit comprises an aircraft air duct.
15 . An aircraft comprising:
the water supply system of claim 1 .
16 . A water supply system for use in an aircraft, the water supply system comprising:
a central water tank comprising a fluid inlet and a fluid outlet;
a supply conduit configured to permit fluid flow from the fluid outlet of the central water tank to a user equipment;
wherein at least a section of the supply conduit is connected and thermally coupled to an aircraft auxiliary conduit so as to enable a transfer of thermal energy to the supply conduit therefrom to maintain a temperature of water in the supply conduit above a freezing temperature thereof;
wherein the supply conduit is disposed between the aircraft auxiliary conduit and a thermal insulator extending circumferentially around the aircraft auxiliary conduit; or
wherein the supply conduit is disposed in a discontinuity of a thermal insulator extending circumferentially discontinuously around the aircraft auxiliary conduit; or
wherein the supply conduit is located externally of a thermal insulator extending circumferentially around an aircraft auxiliary conduit.