Thermally-actuated flow-restrictor device for aircraft beverage maker

Patent metadata

Field	Value
Publication number	US-10383475-B2
Application number	US-201615250512-A
Country	US
Kind code	B2
Filing date	Aug 29, 2016
Priority date	Sep 1, 2015
Publication date	Aug 20, 2019
Grant date	Aug 20, 2019

Abstract

A thermally-actuated flow-restrictor device in an aircraft galley insert is provided that includes a housing formed of first and second flanged fittings. The first fitting includes an outlet port for connection to an aircraft galley insert, and the second fitting includes an inlet port for connection to an aircraft potable water supply. The second fitting also includes a boss surrounding the inlet port. A closure element contained within the housing includes a plurality of metals having different coefficients of thermal expansion. This allows the element to actuate depending upon the temperature of water contacting the closure element. When water having a predetermined temperature contacts the closure element, its surface facing the inlet port becomes convexly positioned proximal to the boss, thereby restricting the backflow of water through the flow-restrictor device. Once the closure element cools, its surface facing the inlet port becomes concave, resulting in normal device operation.

First claim

What is claimed is:

1. A thermally-actuated flow-restrictor device for an aircraft galley insert, the flow- restrictor device comprising:
a housing including a first flanged fitting and a second flanged fitting, the first flanged fitting including an outlet port configured to connect in fluid communication with the aircraft galley insert, and the second flanged fitting including an inlet port configured to connect in fluid communication with an aircraft potable water supply;
a closure element contained within the housing, the closure element including one or more apertures for water to flow within the housing from the inlet port to the outlet port, the closure element having a surface facing the inlet port that is concave when the closure element is at ambient temperature to allow water to flow through the closure element from the inlet port to the outlet port;
wherein the closure element includes a plurality of metals each having a different coefficient of thermal expansion which allow the surface of the closure element facing the inlet port to become convex when water having a predetermined temperature contacts the closure element and that allow the surface of the closure element to return to being concave when the closure element cools toward ambient temperature; and
wherein when the surface of the closure element is convex, the surface is proximal to a boss concentrically surrounding the inlet port with a gap between the surface and the boss such that the boss does not contact the surface, thereby restricting the backflow of water in the housing from the outlet port to the inlet port while maintaining some access for water to flow to or from the inlet port.

2. The thermally-actuated flow-restrictor device of claim 1 , wherein the closure element is bimetal.

3. The thermally-actuated flow-restrictor device of claim 2 , wherein the closure element is a disc.

4. The thermally-actuated flow-restrictor device of claim 1 , further comprising a seal located within the housing.

5. The thermally-actuated flow-restrictor device of claim 4 , wherein the seal is an O-ring.

6. The thermally-actuated flow-restrictor device of claim 1 , wherein the predetermined temperature is at least 120 degrees Fahrenheit.

7. The thermally-actuated flow-restrictor device of claim 1 , wherein the flow- restrictor device is configured to be installed in a water inlet line of the aircraft galley insert between a water inlet fitting and a water tank of the aircraft galley insert.

8. The thermally-actuated flow-restrictor device of claim 1 , wherein the flow- restrictor device is configured to be installed in one of a water inlet fitting and a water tank of the aircraft galley insert.

9. The thermally-actuated flow-restrictor device of claim 1 , further comprising a fastener arrangement in the housing for fastening the first flanged fitting to the second flanged fitting.

10. A thermally-actuated flow-restrictor device for an aircraft galley insert, the flow- restrictor device comprising:
a housing including a first flanged fitting and a second flanged fitting, the first flanged fitting including an outlet port configured to connect in fluid communication with the aircraft galley insert, and the second flanged fitting including an inlet port configured to connect in fluid communication with an aircraft potable water supply;
a closure element contained within the housing, the closure element including one or more apertures for water to flow within the housing from the inlet port to the outlet port, the closure element having a surface facing the inlet port that is concave when the closure element is at ambient temperature to allow water to flow through the closure element from the inlet port to the outlet port;
wherein the closure element is a disc that includes a plurality of metals each having a different coefficient of thermal expansion which allow the surface of the closure element facing the inlet port to become convex when water having a predetermined temperature contacts the closure element and which allows the surface of the closure element to return to being concave when the closure element cools toward ambient temperature; and
wherein when the surface of the closure element is convex, the surface is proximal to a boss concentrically surrounding the inlet port with a gap between the surface and the boss such that the boss does not contact the surface, thereby restricting the backflow of water in the housing from the outlet port to the inlet port while maintaining some access for water to flow to or from the inlet port.

11. The thermally-actuated flow-restrictor device of claim 10 , wherein the closure element is bimetal.

12. The thermally-actuated flow-restrictor device of claim 10 , further comprising a seal located within the housing.

13. The thermally-actuated flow-restrictor device of claim 12 , wherein the seal is an O-ring.

14. The thermally-actuated flow-restrictor device of claim 10 , wherein the predetermined temperature is at least 120 degrees Fahrenheit.

15. The thermally-actuated flow-restrictor device of claim 10 , wherein the flow- restrictor device is configured to be installed in a water inlet line of the aircraft galley insert between a water inlet fitting and a water tank of the aircraft galley insert.

16. The thermally-actuated flow-restrictor device of claim 10 , wherein the flow- restrictor device is configured to be installed in one of a water inlet fitting and a water tank of the aircraft galley insert.

17. The thermally-actuated flow-restrictor device of claim 10 , further comprising a fastener arrangement in the housing for fastening the first flanged fitting to the second flanged fitting.

18. A thermally-actuated flow-restrictor device for an aircraft galley insert, the flow-restrictor device comprising:
a housing including a first flanged fitting and a second flanged fitting, the first flanged fitting including an outlet port configured to connect in fluid communication with the aircraft galley insert, and the second flanged fitting including an inlet port configured to connect in fluid communication with an aircraft potable water supply, wherein a seal is contained within the housing;
a closure element contained within the housing, the closure element including one or more apertures for water to flow within the housing from the inlet port to the outlet port, the closure element having a surface facing the inlet port that is concave when the closure element is at ambient temperature to allow water to flow through the closure element from the inlet port to the outlet port;
wherein the closure element is a disc that includes a plurality of metals each having a different coefficient of thermal expansion which allow the surface of the closure element facing the inlet port to become convex when water having a predetermined temperature contacts the closure element and which allows the surface of the closure element to return to being concave when the closure element cools toward ambient temperature; and
wherein when the surface of the closure element is convex, the surface is proximal to a boss concentrically surrounding the inlet port with a gap between the surface and the boss such that the boss does not contact the surface, thereby restricting the backflow of water in the housing from the outlet port to the inlet port while maintaining some access for water to flow to or from the inlet port.

Assignees

• Be Aerospace Inc

Inventors

• Dietz Stuart A
• Crosswait Craig
• Aeschliman Dan
• Kelly Luke E

Classifications

• A47J31/461 Primary

  Valves, e.g. drain valves · CPC title

• F16K31/002

  actuated by temperature variation (thermo-electric F16K31/025) · CPC title

• A47J31/58

  Safety devices · CPC title

• B64D11/04

  Galleys · CPC title

• A47J31/46 Primary

  Dispensing spouts, pumps, drain valves or like liquid transporting devices · CPC title