Cryogenic liquid oxidizer cooled high energy system

• US 20060078034A1
• Filed: 05/18/2005
• Published: 04/13/2006
• Est. Priority Date: 06/18/2004
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Coffinberry, George Albert
• Granted Patent: US 7,406,829 B2
• Time in Patent Office: Days
• US Class Current: 372/109
• CPC Class Codes: F02C 1/00 Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid by the use of combustion products F02C3/00, F02C5/00
• CPC Class Codes: F41B 6/00 Electromagnetic launchers ; Plasma-actuated launchers projectiles for electromagnetic or plasma guns F42B6/006
• CPC Class Codes: F41H 13/0043 Directed energy weapons, i.e. devices that direct a beam of high energy content toward a target for incapacitating or destroying the target
• CPC Class Codes: H02K 55/02 of the synchronous type
• CPC Class Codes: H02K 7/1823 structurally associated with turbines or similar engines
• CPC Class Codes: H02K 9/20 wherein the cooling medium vaporises within the machine casing
• CPC Class Codes: Y02E 40/60 Superconducting electric elements or equipment; Power systems integrating superconducting elements or equipment

Abstract

A high energy system comprising a high energy electrical device powered by an electrical generator both of which are cooled by a cryogenic liquid oxidant stored in a storage tank. A power turbine powered by a combustor using fuel and the oxidant drives the electrical generator. A turbopump powered by a portion of exhaust flow from the power turbine pumps the cryogenic liquid oxidant from the storage tank to the generator and the device. In an exemplary embodiment of the system, the electrical device is a directed energy weapon, uses liquid air as the liquid oxidant, and uses a variable geometry turbine nozzle in the power turbine. A reheater may be used between a high pressure turbine and a lower pressure turbine of the power turbine. Compressor bleed from a gas turbine engine may provide air augmentation to the power turbine.

Claims

1. A high energy system comprising:

a high energy electrical device,

an electrical generator in power supply relationship to the device,

a cryogenic storage tank in cooling supply relationship to the electrical generator and the high energy electrical device,

a combustor in oxidant receiving relationship with the high energy electrical device,

a power turbine drivingly connected to the electrical generator and in working fluid receiving relationship with the combustor,

a turbopump including a turbopump turbine drivingly connected to a pump and operable to pump a cryogenic fluid oxidant from the storage tank to the generator and the device, and

the turbopump turbine in turbine exhaust flow receiving relationship with the power turbine.

2. A system as claimed in claim 1 further comprising a variable geometry turbine nozzle in the power turbine.

3. A system as claimed in claim 1 further comprising at least two turbine stages.

4. A system as claimed in claim 3 further comprising a variable geometry turbine nozzle in the turbine.

5. A system as claimed in claim 1 further comprising a high pressure turbine and a lower pressure turbine in the power turbine.

6. A system as claimed in claim 5 further comprising a variable geometry turbine nozzle in the power turbine.

7. A system as claimed in claim 6 further comprising a gas turbine engine including an air compressor in selective bleed air supply communication with the lower pressure turbine.

8. A system as claimed in claim 7 further comprising a reheater between the high pressure turbine and the lower pressure turbine.

9. A system as claimed in claim 1 further comprising liquid air stored in the cryogenic storage tank.

10. A system as claimed in claim 9 further comprising a variable geometry turbine nozzle in the power turbine.

11. A system as claimed in claim 9 further comprising a high pressure turbine and a lower pressure turbine in the power turbine.

12. A system as claimed in claim 11 further comprising a variable geometry turbine nozzle in the power turbine.

13. A system as claimed in claim 12 further comprising a gas turbine engine including an air compressor in selective bleed air supply communication with the lower pressure turbine.

14. A system as claimed in claim 12 further comprising a reheater between the high pressure turbine and the lower pressure turbine.

15. A system as claimed in claim 1 further comprising liquid air stored in the cryogenic storage tank and the device being a directed energy weapon.

16. A system as claimed in claim 15 further comprising a variable geometry turbine nozzle in the power turbine.

17. A system as claimed in claim 15 further comprising a high pressure turbine and a lower pressure turbine in the power turbine and a variable geometry turbine nozzle in the power turbine.

18. A system as claimed in claim 17 further comprising a gas turbine engine including an air compressor in selective bleed air supply communication with the lower pressure turbine.

19. A system as claimed in claim 18 further comprising a reheater between the high pressure turbine and the lower pressure turbine.

20. A system as claimed in claim 19 wherein the generator is a superconducting generator.

21. A system as claimed in claim 15 further comprising:

the weapon system being mounted in a gas turbine engine powered aircraft, and

the storage tank being operable to alternatively store the cryogenic fluid oxidant and gas turbine engine fuel to power the aircraft during a single mission of the aircraft.

22. A system as claimed in claim 21 further comprising aircraft and the storage tank being operable to store and partially fuel the gas turbine engine as the aircraft flies to a target area then fill the storage tank with the cryogenic fluid oxidant, then operate the weapon system using the cryogenic fluid oxidant.