Cooling system for high-speed vehicles and method of cooling high-speed vehicles

• US 7,963,100 B2
• Filed: 05/25/2006
• Issued: 06/21/2011
• Est. Priority Date: 05/25/2005
• Status: Active Grant

• Current Assignee: Northrop Grumman Systems Corporation (Northrop Grumman Corporation)
• Original Assignee: Alliant Techsystems Incorporated (Northrop Grumman Corporation)
• Inventors: Tyll, Jason S., Bakos, Robert J., Balepin, Vladimir V., Castrogiovanni, Anthony
• Primary Examiner(s): Kim; Ted
• Application Number:
  US11/442,677
• Publication Number:
  US 20070006594A1
• Time in Patent Office: 1,853 Days
• Field of Search: 602/66, 602/67, 607/30, 60/391.81, 607/68, 244/135.R
• US Class Current: 60/267
• CPC Class Codes: F02K 1/822 Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A cooling system for a high-speed vehicle may comprise a combustor wall at least partially enclosing a combustor and which is cooled using a coolant circulating in a Brayton cycle. The heated coolant may be expanded in a turbine, transfer heat to a fuel within a heat exchanger, and be compressed by a compressor before returning to the combustor wall. The combustor wall may be capable of withstanding high temperatures, higher than the temperature at which fuel coking may take place. Heat transfer takes place between the coolant and the combustor wall, and between the coolant and the fuel. A method of cooling an engine for a high-speed vehicle is also disclosed.

Claims

1. A cooling system for a scramjet engine, comprising:

a heat exchanger configured for heat exchange between a first fluid and a second fluid;

a first fluid line for transfer of the first fluid between the heat exchanger and a combustor of the scramjet engine; and

a closed-loop comprising a second fluid line for transfer of the second fluid sequentially from the heat exchanger to a compressor, from the compressor to a wall, the wall at least partially enclosing the combustor of the scramjet engine, from the wall to a turbine, and from the turbine to the heat exchanger.

2. The cooling system of claim 1, wherein the compressor is mechanically connected to and driven by the turbine.

3. The cooling system of claim 2, wherein the turbine is mechanically coupled to an electric power generator.

4. The cooling system of claim 1, wherein the second fluid comprises one of helium, hydrogen, nitrogen, xenon or mixtures thereof.

5. The cooling system of claim 1, wherein the first fluid comprises a fuel for the scramjet engine.

6. The cooling system of claim 1, wherein the closed-loop further comprises a bypass line around the compressor.

7. The cooling system of claim 1, wherein the closed-loop further comprises a bypass line around the wall at least partially enclosing the combustor.

8. The cooling system of claim 1, wherein the closed-loop further comprises a bypass line around the heat exchanger.

9. The cooling system of claim 1, wherein the closed-loop further comprises a bypass line around both the turbine and the heat exchanger.

10. The cooling system of claim 1, wherein the first fluid line further comprises:

a passageway through a fuel pump having an inlet and an outlet;

a bypass line in communication with the fuel pump inlet and the fuel pump outlet; and

a valve disposed in the bypass line.

11. The cooling system of claim 1, further comprising a fluid source in communication with the second fluid line and configured to selectively provide a flow of fluid through the second fluid line.

12. The cooling system of claim 11, further comprising a fluid sink in communication with the second fluid line and configured to selectively receive a flow of fluid from the second fluid line.

13. A cooling system for a scramjet engine, comprising:

a heat exchanger configured for heat exchange between a first fluid and a second fluid;

a fuel flow path comprising a first fluid line for transfer of the first fluid between the heat exchanger and a combustor of the scramjet engine; and

a closed-loop coolant flow path comprising a second fluid line for transfer of the second fluid sequentially from the heat exchanger to a compressor, from the compressor to a wall, the wall at least partially enclosing the combustor of the scramjet engine, from the wall to a turbine, and from the turbine to the heat exchanger.

14. The cooling system of claim 13, wherein the compressor is mechanically connected to and driven by the turbine.

15. The cooling system of claim 13, wherein the turbine is mechanically coupled to an electric power generator.

16. The cooling system of claim 13, wherein the closed-loop coolant flow path further comprises a bypass line around the compressor.

17. The cooling system of claim 13, wherein the closed-loop coolant flow path further comprises a bypass line around the wall at least partially enclosing the combustor.

18. The cooling system of claim 13, wherein the closed-loop coolant flow path further comprises a bypass line around the heat exchanger.

19. The cooling system of claim 13, wherein the closed-loop coolant flow path further comprises a bypass line around both the turbine and the heat exchanger.

20. The cooling system of claim 13, wherein the fuel flow path further comprises:

a passageway through a fuel pump having an inlet and an outlet;

a bypass line in communication with the fuel pump inlet and the fuel pump outlet; and

a valve disposed in the bypass line.

21. The cooling system of claim 13, further comprising a fluid source in communication with the second fluid line and configured to selectively provide a flow of fluid through the second fluid line.

22. The cooling system of claim 21, further comprising a fluid sink in communication with the second fluid line and configured to selectively receive a flow of fluid from the second fluid line.