Aircraft air duct system for transmitting power and light

Patent metadata

Field	Value
Publication number	US-12030646-B2
Application number	US-202218057900-A
Country	US
Kind code	B2
Filing date	Nov 22, 2022
Priority date	Feb 5, 2020
Publication date	Jul 9, 2024
Grant date	Jul 9, 2024

Abstract

An air duct system includes an air duct having a main body. The main body of the air duct defines a passageway and an outer surface. The air duct system also includes one or more thermoelectric generators. Each thermoelectric generator includes a hot side and a cold side, and the hot side of the thermoelectric generator is positioned along the outer surface of the air duct.

First claim

What is claimed is:

1. An air duct system for an aircraft, comprising:
an air duct having a main body, wherein the main body of the air duct defines a passageway and an outer surface, wherein the passageway includes a reflective inner surface and the air duct receives conditioned air that is created by mixing cooled bleed air with recirculated air;
a visible light source configured to generate visible light, wherein the visible light source directs the visible light along the reflective inner surface of the air duct, and wherein heat is generated as the visible light impinges against the reflective inner surface of the air duct; and
one or more thermoelectric generators, wherein each thermoelectric generator includes a hot side and a cold side, and the hot side of the thermoelectric generator is positioned along the outer surface of the air duct, and wherein the thermoelectric generator is configured to transform the heat into electrical energy.

2. The air duct system of claim 1 , wherein the one or more thermoelectric generators are cooled by natural convection, forced convection, or solid conduction.

3. The air duct system of claim 1 , wherein the one or more thermoelectric generators each include a heat sink, and wherein the cold side of the one or more thermoelectric generators contact the heat sink.

4. The air duct system of claim 1 , wherein the one or more thermoelectric generators are each a solid-state thermoelectric module.

5. The air duct system of claim 1 , wherein the one or more thermoelectric generators are cooled by solid conduction.

6. The air duct system of claim 5 , wherein a solid connects the cold side of at least one of the one or more thermoelectric generators to outside air.

7. The air duct system of claim 6 , wherein the solid is constructed of one or more of the following: aluminum, graphene, and single wall carbon nanotubes.

8. The air duct system of claim 6 , wherein the solid is a heat pipe.

9. The air duct system of claim 1 , further comprising an ultraviolet light source configured to generate ultraviolet light, wherein the ultraviolet light source directs the ultraviolet light along the reflective inner surface of the air duct.

10. The air duct system of claim 1 , wherein the visible light source includes an array of light-emitting diodes (LEDs).

11. The air duct system of claim 1 , wherein the visible light source is positioned at an end of the air duct situated at the front end of the aircraft.

12. An air duct system for an aircraft, comprising:
an air duct having a main body, wherein the main body of the air duct defines an outer surface and a passageway having a reflective inner surface and the air duct receives conditioned air that is created by mixing cooled bleed air with recirculated air;
a visible light source configured to generate visible light, wherein the visible light source directs the visible light along the reflective inner surface of the air duct and wherein heat is generated as the visible light impinges against the reflective inner surface of the air duct;
a thermoelectric generator having a hot side and a cold side, wherein the hot side of the thermoelectric generator is positioned along the outer surface of the air duct, and wherein the thermoelectric generator is configured to transform the heat into electrical energy;
an emitter configured to emit radio frequency waves, wherein the emitter directs the radio frequency waves along the reflective inner surface of the air duct; and
one or more antennas that are each connected to a corresponding power harvesting circuit, wherein the radio frequency waves are received by the one or more antennas and are converted into electrical power by the corresponding power harvesting circuit.

13. The air duct system of claim 12 , wherein the thermoelectric generator is cooled by natural convection, forced convection, or solid conduction.

14. The air duct system of claim 12 , wherein the thermoelectric generator is a solid-state thermoelectric module.

15. The air duct system of claim 12 , wherein the thermoelectric generator includes a heat sink, and wherein the cold side of the thermoelectric generator contacts the heat sink.

16. The air duct system of claim 12 , wherein the thermoelectric generator is cooled by solid conduction.

17. The air duct system of claim 16 , wherein a solid connects the cold side of the thermoelectric generator to outside air.

18. The air duct system of claim 17 , wherein the solid is constructed of one or more of the following: aluminum, graphene, and single wall carbon nanotubes.

19. The air duct system of claim 17 , wherein the solid is a heat pipe.

20. A method for transmitting air, visible light, and electrical power through an air duct of an aircraft, the method comprising:
receiving, by the air duct, conditioned air, and visible light, wherein the conditioned air is created by mixing cooled bleed air with recirculated air;
directing the visible light along a reflective inner surface of the air duct, wherein the visible light reflects off of the reflective inner surface and travels along a passageway of the air duct, and wherein heat is generated as the visible light impinges against the reflective inner surface of the air duct;
transforming, by a thermoelectric generator positioned along an outer surface of the air duct, the heat generated as the visible light impinges against the reflective inner surface of the air duct into electrical energy that is consumed by the aircraft;
emitting radio frequency waves by an emitter, wherein the radio frequency waves are directed along the reflective inner surface of the air duct, and wherein further heat is generated as the radio frequency waves impinge against the reflective inner surface of the air duct;
transforming, by the thermoelectric generator, the further heat generated as the radio frequency waves impinge against the reflective inner surface of the air duct into electrical energy that is consumed by the aircraft;
receiving the radio frequency waves by one or more antennas, wherein the one or more antennas are each connected to a corresponding power harvesting circuit; and
converting the radio frequency waves into electrical power by the corresponding power harvesting circuit.

Assignees

• Boeing Co

Inventors

• Hiller Nathan D

Classifications

• B64D13/06 Primary

  the air being conditioned (pressurising B64D13/02) · CPC title

• F21V7/0008 Primary

  providing for indirect lighting · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• H10N10/13

  characterised by the heat-exchanging means at the junction · CPC title

• A61L9/20

  Ultraviolet radiation · CPC title