THERMAL MANAGEMENT SYSTEM AND METHOD OF ASSEMBLING THE SAME

• US 20150068703A1
• Filed: 09/06/2013
• Published: 03/12/2015
• Est. Priority Date: 09/06/2013
• Status: Abandoned Application

• Current Assignee: GE Aviation Systems LLC (GE Aerospace), General Electric Company
• Original Assignee: GE Aviation Systems LLC (GE Aerospace), General Electric Company
• Inventors: de Bock, Hendrik Pieter Jacobus, Dunsdon, Jonathan Mark, Engelhardt, Michel
• Application Number:
  US14/020,506
• Publication Number:
  US 20150068703A1
• Time in Patent Office: Days
• US Class Current: 165/41
• CPC Class Codes: B64D 13/00 Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space , or structural parts of the aircraft treatment rooms with artificial climate for medical purposes A61G10/02; respiratory apparatus in general A62B; for vehicles in general B60H
• CPC Class Codes: B64D 2013/0607 providing hot air or liquid for deicing aircraft parts, e.g. aerodynamic surfaces or windows
• CPC Class Codes: F28D 15/0233 the conduits having a particular shape, e.g. non-circular cross-section, annular F28D15/0241, F28D15/0266 take precedence
• CPC Class Codes: F28D 15/0266 with separate evaporating and condensing chambers connected by at least one conduit; Loop-type heat pipes; with multiple or common evaporating or condensing chambers F28D15/043 takes precedence
• CPC Class Codes: F28D 15/0275 Arrangements for coupling heat-pipes together or with other structures, e.g. with base blocks; Heat pipe cores
• CPC Class Codes: F28D 15/046 characterised by the material or the construction of the capillary structure
• CPC Class Codes: F28D 2015/0216 having particular orientation, e.g. slanted, or being orientation-independent
• CPC Class Codes: F28F 2210/02 with particular branching, e.g. fractal conduit arrangements
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency

Abstract

A thermal management system for cooling a heat source onboard an aircraft that has a frame and a skin coupled to the frame such that the skin has a first segment and a second segment includes a first network of heat pipes coupled in conductive heat transfer with the heat source and the first segment of skin. The first network of heat pipes is configured to heat the first segment of skin using heat from the heat source. The thermal management system further includes a second network of heat pipes coupled in conductive heat transfer with the heat source and the second segment of skin. The second network of heat pipes is configured to heat the second segment of skin using heat from the heat source. The thermal management system is configured to selectively deactivate the first network of heat pipes and the second network of heat pipes.

Claims

1. A thermal management system for cooling a heat source onboard an aircraft having a frame and a skin coupled to the frame such that the skin includes a first segment and a second segment, said thermal management system comprising:

a first network of heat pipes coupled in conductive heat transfer with the heat source and the first segment of the skin, said first network of heat pipes configured to heat the first segment of the skin using heat from the heat source; and

a second network of heat pipes coupled in conductive heat transfer with the heat source and the second segment of the skin, said second network of heat pipes configured to heat the second segment of the skin using heat from the heat source, wherein said thermal management system is configured to selectively deactivate said first network of heat pipes and said second network of heat pipes.

2. The thermal management system in accordance with claim 1, wherein the heat source onboard the aircraft is an electronic heat dissipating source, and wherein said thermal management system further comprises a thermal rail coupled in conductive heat transfer with the electronic heat dissipating source, said first network of heat pipes, and said second network of heat pipes.

3. The thermal management system in accordance with claim 1, wherein each of said first network of heat pipes and said second network of heat pipes comprises a plurality of sealed, two-phase capillary heat pipes.

4. The thermal management system in accordance with claim 1, wherein said first network of heat pipes and said second network of heat pipes are integrated into the frame of the aircraft.

5. The thermal management system in accordance with claim 1, wherein the aircraft has a fuel-containing structure, and wherein said thermal management system further comprises a third network of heat pipes coupled in conductive heat transfer with the heat source and fuel inside of the fuel-containing structure.

6. The thermal management system in accordance with claim 5, wherein the fuel-containing structure is a fuel tank, said third network of heat pipes coupled in conductive heat transfer with the fuel tank.

7. The thermal management system in accordance with claim 5, wherein at least one heat pipe of said third network of heat pipes is inserted directly into the fuel inside of the fuel-containing structure.

8. The thermal management system in accordance with claim 7, wherein said at least one heat pipe comprises a plurality of miniature fins configured to interface with the fuel.

9. The thermal management system in accordance with claim 5, further comprising a heat exchanger configured to exchange heat between the fuel and said third network of heat pipes.

10. The thermal management system in accordance with claim 5, wherein at least one heat pipe of said third network of heat pipes is integrated into a wall of the fuel-containing structure.

11. The thermal management system in accordance with claim 1, wherein at least one of said first network of heat pipes and said second network of heat pipes is arranged in a herringbone-type configuration.

12. The thermal management system in accordance with claim 1, further comprising a thermal energy storage element associated with at least one of said first network of heat pipes and said second network of heat pipes.

13. The thermal management system in accordance with claim 1, wherein each of said first network of heat pipes and said second network of heat pipes comprises a variable conductance heat pipe to facilitate the selective deactivation.

14. The thermal management system in accordance with claim 13, further comprising a reservoir of gas in flow communication with said variable conductance heat pipe such that when the gas is heated the associated network of heat pipes is deactivated.

15. The thermal management system in accordance with claim 14, wherein the gas is one of an argon gas and a helium gas.

16. The thermal management system in accordance with claim 14, further comprising an electric heater coupled to said reservoir of gas.

17. The thermal management system in accordance with claim 1, further comprising a processing unit configured to selectively deactivate each of said first network of heat pipes and said second network of heat pipes to alter an infrared signature of the aircraft.

18. An aircraft comprising the thermal management system according to claim 1.

19. A method of assembling a thermal management system for cooling a heat source onboard an aircraft having a frame and a skin coupled to the frame such that the skin includes a first segment and a second segment, said method comprising:

coupling a first network of heat pipes in conductive heat transfer with the heat source and the first segment of the skin, the first network of heat pipes configured to heat the first segment of the skin using heat from the heat source;

coupling a second network of heat pipes in conductive heat transfer with the heat source and the second segment of the skin, the second network of heat pipes configured to heat the second segment of the skin using heat from the heat source; and

coupling a processing unit to the first network of heat pipes and the second network of heat pipes, the processing unit configured to selectively deactivate the first network of heat pipes and the second network of heat pipes.

20. A thermal management system for cooling a heat source onboard an aircraft having a frame and a skin coupled to the frame, said thermal management system comprising a network of heat pipes configured to transfer heat from the heat source to the skin by conductive heat transfer between adjacent heat pipes.