Rotary valve for pulse detonation engines

• US 6,505,462 B2
• Filed: 03/29/2001
• Issued: 01/14/2003
• Est. Priority Date: 03/29/2001
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Meholic, Gregory Vincent
• Primary Examiner(s): Freay, Charles G.
• Assistant Examiner(s): Belena, John F
• Application Number:
  US09/821,274
• Publication Number:
  US 20020139106A1
• Time in Patent Office: 656 Days
• Field of Search: 60/393.9, 60/393.8, 607/26, 605/32
• US Class Current: 60/39.39
• CPC Class Codes: F02C 5/12 the combustion chambers having inlet or outlet valves, e.g. Holzwarth gas-turbine plants
• CPC Class Codes: F02K 7/06 with combustion chambers having valves
• CPC Class Codes: F02K 7/075 with multiple pulse-jet engines
• CPC Class Codes: F05D 2250/411 in rotation

Abstract

A rotary valve for pulse detonation engines includes a rotor rotatively mounted in the forward end of the pulse detonation tube and a plurality of transfer plenums for receiving fuel and air arranged around the rotor and partially disposed over the forward end of the tube. The rotor has a plurality of internal flow passages formed therein which periodically align with a plurality of inlet ports formed near the forward end of the tube as the rotor rotates. Each one of the transfer plenums is aligned with a corresponding one of the inlet ports so that the flow passages will establish fluid communication between the tube and the transfer plenums when aligned with the inlet ports. Additional features include axial injection of the fuel-air mixture into the pulse detonation tube, pre-compression of the inlet flow and a drive system located outside of the primary gas path.

Claims

1. In a pulse detonation engine including a tube having a forward end and an aft end, a rotary valve comprising:

a rotor rotatively mounted in said forward end of said tube, said rotor having a plurality of internal flow passages formed therein; and

a plurality of transfer plenums for receiving fuel and air arranged around said rotor, wherein said flow passages will periodically establish fluid communication between said tube and said transfer plenums as said rotor rotates.

2. The rotary valve of claim 1 wherein there are equal numbers of said internal flow passages and said transfer plenums.

3. The rotary valve of claim 1 further comprising an inlet for introducing a fluid to said transfer plenums.

4. The rotary valve of claim 3 further comprising a compressor rotatively mounted in said inlet for pressurizing said fluid.

5. The rotary valve of claim 4 further comprising an axle that drivingly engages said rotor and said compressor.

6. The rotary valve of claim 5 further comprising means for rotating said axle.

7. The rotary valve of claim 6 wherein said means for rotating said axle comprise a drive shaft, a first gear fixedly mounted to said drive shaft, and a second gear fixedly mounted to said axle and meshing with said first gear.

8. The rotary valve of claim 7 further comprising a housing containing said axle and said first and second gears.

9. The rotary valve of claim 3 wherein said fluid introduced to said transfer plenums via said inlet is a fuel-air mixture.

10. The rotary valve of claim 3 wherein said fluid introduced to said transfer plenums via said inlet is air.

11. The rotary valve of claim 10 further comprising a plurality of fuel injectors for directly injecting fuel directly into said transfer plenums.

12. A pulse detonation engine comprising:

a tube having a forward end and an open aft end, and a plurality of inlet ports formed therein near said forward end;

a rotor rotatively mounted in said forward end of said tube, said rotor having a plurality of internal flow passages formed therein; and

a plurality of transfer plenums for receiving fuel and air arranged around said rotor and partially disposed over said forward end of said tube, each one of said transfer plenums being aligned with a corresponding one of said inlet ports, wherein said flow passages will periodically align with said inlet ports and establish fluid communication between said tube and said transfer plenums as said rotor rotates.

13. The pulse detonation engine of claim 12 further comprising an igniter disposed in said tube adjacent to said rotor.

14. The pulse detonation engine of claim 12 further comprising an annular ridge formed on an inner surface of said tube and overlapping said rotor so as to provide a seal between said rotor and said tube.

15. The pulse detonation engine valve of claim 12 wherein there are equal numbers of said internal flow passages and said transfer plenums.

16. The pulse detonation engine of claim 12 further comprising an inlet for introducing a fluid to said transfer plenums.

17. The pulse detonation engine of claim 16 further comprising a compressor rotatively mounted in said inlet for pressurizing said fluid.

18. The pulse detonation engine of claim 17 further comprising an axle that drivingly engages said rotor and said compressor.

19. The pulse detonation engine of claim 18 further comprising means for rotating said axle.

20. The pulse detonation engine of claim 19 wherein said means for rotating said axle comprise a drive shaft, a first gear fixedly mounted to said drive shaft, and a second gear fixedly mounted to said axle and meshing with said first gear.

21. The pulse detonation engine of claim 20 further comprising a housing containing said axle and said first and second gears.

22. The pulse detonation engine of claim 16 wherein said fluid introduced to said transfer plenums via said inlet is a fuel-air mixture.

23. The pulse detonation engine of claim 16 wherein said fluid introduced to said transfer plenums via said inlet is air.

24. The pulse detonation engine of claim 23 further comprising a plurality of fuel injectors for directly injecting fuel directly into said transfer plenums.