METHOD AND APPARATUS FOR TAILORING THE EQUIVALENCE RATIO IN A VALVED PULSE DETONATION COMBUSTOR

• US 20090139203A1
• Filed: 11/14/2008
• Published: 06/04/2009
• Est. Priority Date: 11/15/2007
• Status: Abandoned Application

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Chapin, David, Rasheed, Adam, Kenyon, Ross Hartley, Pinard, Pierre Francois, Hinckley, Kevin
• Application Number:
  US12/271,091
• Publication Number:
  US 20090139203A1
• Time in Patent Office: Days
• US Class Current: 60/247
• CPC Class Codes: F02C 5/02 characterised by the arrangement of the combustion chamber in the chamber in the plant combustion chambers per se F23R
• CPC Class Codes: F23R 7/00 Intermittent or explosive combustion chambers

Abstract

A pulse detonation combustor assembly contains at least one PDC tube, a mechanical air flow valve which directs an air flow into the PDC tube, where the mechanical air flow assembly changes a rate of the air flow into the PDC tube during a fill stage of the PDC tube. The assembly also contains a fuel flow control valve which directs fuel to the PDC tube and changes the rate of the fuel flow into PDC tube. By controlling the flow of the fuel and air into the PDC tube the equivalence ratio profile of the PDC tube can be tailored and controlled.

Claims

1. A pulse detonation combustion system, comprising:

at least one pulse detonation combustor tube;

an air flow valve which directs an air flow into said at least one pulse detonation combustor tube, wherein said air flow assembly changes a rate of change of said air flow into said pulse detonation combustor tube during a fill stage of said pulse detonation combustor tube;

a fuel flow control valve which directs fuel to said at least one pulse detonation combustor tube; and

wherein said air flow valve controls said air flow rate of change with respect to a fuel flow rate of change provided by said fuel flow control valve to control the equivalence ratio within said pulse detonation combustor tube.

2. The pulse detonation combustion system of claim 1, wherein said air flow valve comprises a rotating portion having at least one air flow port through which said air flow passes into said at least one pulse detonation combustor tube, and

wherein rotation of said rotating portion controls said equivalence ratio within said at least one pulse detonation combustor tube.

3. The pulse detonation combustion system of claim 2, wherein said at least one air flow port has a main portion and at least one of a leading edge portion and a trailing edge portion extending from said main portion, wherein said main portion has a shape which corresponds to a shape of an inlet to said at least one pulse detonation tube.

4. The pulse detonation combustion system of claim 3, wherein said main portion substantially dimensionally matches said inlet.

5. The pulse detonation combustion system of claim 3, wherein said either leading edge or trailing edge has an edge contour which matches a contour of said inlet.

6. The pulse detonation combustion system of claim 2, wherein rotation of said rotating portion controls said flow rate of change of said air into said at least one pulse detonation combustor tube with respect to a fuel flow rate of change from said fuel flow control valve.

7. The pulse detonation combustion system of claim 2, wherein said rotating portion comprises a plurality of said air flow ports.

8. The pulse detonation combustion system of claim 2, wherein a rate of rotation of said rotating portion changes during a single rotation of said rotating portion to change said rate of change of said air flow.

9. The pulse detonation combustion system of claim 3, wherein said at least one air flow port comprises both a leading edge portion and trailing edge portion and a shape of said leading edge portion is different from a shape of said trailing edge portion.

10. The pulse detonation combustion system of claim 1, further comprising a fuel flow control device which controls a rate change of said fuel flow into said at least one pulse detonation combustor device.

11. The pulse detonation combustion system of claim 2, further comprising a fuel flow control device which controls a rate change of said fuel flow into said at least one pulse detonation combustor device.

12. The pulse detonation combustion system of claim 2, further comprising at least one sensor coupled to said at least one pulse detonation combustor and at least one of a rate of rotation of said rotating portion and a rate of change of said fuel flow is controlled based on feedback from said sensor.

13. The pulse detonation combustion system of claim 1, wherein said rate of change of said air flow is controlled such that said equivalence ratio is rich adjacent to an ignition source within said at least one pulse detonation tube at the end of a fill cycle of said at least one tube.

14. A pulse detonation combustion system, comprising:

at least one pulse detonation combustor tube;

an air flow valve which directs an air flow into said at least one pulse detonation combustor tube, wherein said air flow assembly changes a rate of change of said air flow into said pulse detonation combustor tube during a fill stage of said pulse detonation combustor tube;

a fuel flow control valve which directs fuel to said at least one pulse detonation combustor tube; and

wherein said air flow valve comprises a rotating portion having at least one air flow port through which said air flow passes into said at least one pulse detonation combustor tube,

wherein rotation of said rotating portion controls an equivalence ratio within said at least one pulse detonation combustor tube such that said equivalence ratio is maintained constant for at least 50% of the fill of said at least one pulse detonation combustor.

15. The pulse detonation combustion system of claim 14, wherein said at least one air flow port has a main portion and at least one of a leading edge portion and a trailing edge portion extending from said main portion, wherein said main portion has a shape which corresponds to a shape of an inlet to said at least one pulse detonation tube.

16. The pulse detonation combustion system of claim 15, wherein said main portion substantially dimensionally matches said inlet.

17. The pulse detonation combustion system of claim 15, wherein said either leading edge or trailing edge has an edge contour which matches a contour of said inlet.

18. The pulse detonation combustion system of claim 14, wherein rotation of said rotating portion controls said flow rate change of air into said at least one pulse detonation combustor tube with respect to a fuel flow rate from said fuel flow control valve.

19. The pulse detonation combustion system of claim 14, wherein said rotating portion comprises a plurality of said air flow ports.

20. The pulse detonation combustion system of claim 14, wherein a rate of rotation of said rotating portion changes during a single rotation of said rotating portion to change said rate of change of said air flow.

21. The pulse detonation combustion system of claim 15, wherein said at least one air flow port comprises both a leading edge portion and trailing edge portion and a shape of said leading edge portion is different from a shape of said trailing edge portion.

22. The pulse detonation combustion system of claim 14, further comprising a fuel flow control device which controls a rate of change of fuel flow into said at least one pulse detonation combustor device.

23. The pulse detonation combustion system of claim 14, further comprising at least one sensor coupled to said at least one pulse detonation combustor and at least one of a rate of rotation of said rotating portion and a rate of change of fuel flow is controlled based on feedback from said sensor.

24. The pulse detonation combustion system of claim 14, wherein rotation of said rotating portion controls an equivalence ratio within said at least one pulse detonation combustor tube such that said equivalence ratio is maintained constant for at least 90% of the fill of said at least one pulse detonation combustor.