SYSTEM AND METHOD FOR PASSIVE VALVING FOR PULSE DETONATION COMBUSTORS

• US 20080229756A1
• Filed: 12/01/2006
• Published: 09/25/2008
• Est. Priority Date: 12/01/2006
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Rasheed, Adam, Tangirala, Venkat Eswarlu, Dean, Anthony John, Hinckley, Kevin Michael, Chapin, David Michael, Pinard, Pierre Francois
• Granted Patent: US 8,726,630 B2
• Time in Patent Office: Days
• US Class Current: 60/776
• CPC Class Codes: F02C 5/00 Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
• CPC Class Codes: F02K 7/02 the jet being intermittent, i.e. pulse-jet

Abstract

A pulse detonation device contains a pulse detonation combustor which detonates a mixture of oxidizer and fuel. The fuel is supplied through fuel ducts and the fuel flow is controlled by fuel flow control devices. Oxidizer flow is provided through a main inlet portion and a flow control device directs the oxidizer flow to either the combustor or to a bypass duct, or both. The combustor further contains an ignition source. Each of the flow control devices, fuel flow control devices and ignition source are controlled by a control system to optimize performance at different thrust/power settings for the device.

Claims

1. A pulse detonation device, comprising:

a pulse detonation combustor;

a main inlet portion through which an oxidizer passes coupled to said pulse detonation combustor;

a fuel supply portion coupled to said pulse detonation combustor which supplies fuel to said pulse detonation combustor;

an ignition source coupled to said pulse detonation combustor to ignite a mixture of said fuel and an oxidizer provided from said main inlet portion; and

a control system which controls at least one of a flow of said oxidizer, a flow of said fuel and said ignition source at a plurality of operating conditions of said combustor,

wherein pressure within said pulse detonation combustor regulates said supply of fuel from said fuel supply portion.

2. The pulse detonation device of claim 1, farther comprising a bypass flow duct, wherein said main inlet portion is coupled to both of said pulse detonation combustor and said bypass flow duct.

3. The pulse detonation device of claim 1, wherein said main inlet portion has at least one flow control device which directs flow within said main inlet portion to said pulse detonation combustor.

4. The pulse detonation device of claim 1, wherein said fuel supply portion has a fuel flow device which controls the flow of fuel to said pulse detonation combustor.

5. The pulse detonation device of claim 1, further comprising a sensor coupled to either said pulse detonation device and said pulse detonation combustor, wherein said sensor is also coupled to said control system.

6. The pulse detonation device of claim 5, wherein said control system controls said at least one of said flow of said oxidizer, flow of said fuel and said ignition source based on an output signal from said sensor.

7. The pulse detonation device of claim 5, wherein said sensor detects an amount of unused fuel in an exhaust passing through said exhaust portion.

8. The pulse detonation device of claim 1, wherein said control system controls said at least one of said flow of said oxidizer, flow of said fuel and said ignition source to prevent excess fuel from being added to said combustor at said plurality of operating conditions.

9. The pulse detonation device of claim 1, wherein said control system controls said at least one of said flow of said oxidizer, flow of said fuel and said ignition source at a plurality of operating frequencies of said combustor.

10. The pulse detonation device of claim 1, wherein said control system changes an ignition frequency of said ignition source as said operating conditions change.

11. The pulse detonation device of claim 1, wherein said control system changes an amount of oxidizer flow from said main inlet portion to said combustor as said operating conditions change.

12. The pulse detonation device of claim 1, wherein said control system changes an amount of fuel flow as said operating conditions change.

13. The pulse detonation device of claim 1, wherein said pressure within combustor starts and stops said fuel flow.

14. A pulse detonation device, comprising:

a pulse detonation combustor;

a main inlet portion through which an oxidizer passes coupled to said pulse detonation combustor, said main inlet portion having at least one flow control device which directs at least a portion of said flow of said oxidizer to said pulse detonation combustor;

a fuel supply portion coupled to said pulse detonation combustor which supplies fuel to said pulse detonation combustor;

an ignition source coupled to said pulse detonation combustor to ignite a mixture of said fuel and an oxidizer provided from said main inlet portion; and

a control system which controls at least one of a flow of said oxidizer and said ignition source at a plurality of operating conditions of said combustor,

wherein pressure within said pulse detonation combustor regulates said supply of fuel from said fuel supply portion and said flow from said oxidizer.

15. A method of controlling a pulse detonation combustor;

said method comprising;

operating said pulse detonation combustor at a first operating condition;

changing said pulse detonation combustor from said first operating condition to a second operating condition;

changing at least one of an amount of oxidizer entering said combustor, an amount of fuel entering said combustor, and an ignition frequency of said combustor to effect said change from said first operating condition to said second operating condition; and

regulating said fuel flow to said pulse detonation combustor using pressure within said pulse detonation combustor.

16. The method of claim 15, wherein each of said amount of oxidizer entering said combustor, amount of fuel entering said combustor, and ignition frequency of said combustor are changed to effect said change from said first operating condition to said second operating condition.

17. The method of claim 15, further comprising changing an operational frequency of said combustor to effect said change from said first operating condition to said second operating condition.

18. The method of claim 15, further comprising monitoring an exhaust of said combustor.

19. The method of claim 18, wherein said changing of at least one of said oxidizer amount, fuel amount and ignition frequency is based on results of said monitoring of said exhaust.

20. The method of claim 15, wherein said amount of oxidizer entering said combustor and ignition frequency of said combustor are changed to effect said change from said first operating condition to said second operating condition.

21. The method of claim 15, further comprising starting and stopping said fuel flow to said pulse detonation combustor using pressure within said pulse detonation combustor.

22. The method of claim 15, further comprising causing said fuel to enter said combustor after said oxidizer enters said combustor.

23. A method of controlling a pulse detonation combustor;

said method comprising;

determining if an operating condition of said combustor has changed;

determining if said change requires an increase or a decrease in output from said combustor;

wherein

if said change requires an increase, increasing an amount of at least one of an oxidizer and fuel to said combustor; and

if said change requires a decrease, decreasing an amount of at least one of said oxidizer and fuel to said combustor, and

regulating said fuel flow to said pulse detonation combustor using pressure within said pulse detonation combustor.

24. The method of claim 23, wherein if said change requires an increase, increasing an amount of both said oxidizer and fuel to said combustor;

and if said change requires a decrease, decreasing an amount of both of said oxidizer and fuel to said combustor.

25. The method of claim 23, further comprising changing an ignition frequency of an ignition source in said combustor to effect said change.

26. The method of claim 23, further comprising determining if an excess fuel amount is added to said combustor and controlling said increasing or said decreasing step based on said determination of an excess fuel amount.

27. The method of claim 26, wherein said determination of an excess fuel amount includes sensing an excess fuel amount in an exhaust of said combustor.

28. The method of claim 25, wherein if said change requires an increase, increasing said ignition frequency, and if said change requires a decrease, decreasing said ignition frequency.

29. The method of claim 23, further comprising starting and stopping said fuel flow to said pulse detonation combustor using pressure within said pulse detonation combustor.

30. The method of claim 23, further comprising causing said fuel to enter said combustor after said oxidizer enters said combustor.

31. A method of operating a pulse detonation combustor;

said method comprising;

providing a flow of oxidizer to said pulse detonation combustor;

providing a flow of fuel to said pulse detonation combustor; and

providing an ignition source within said pulse detonation combustor,

wherein said flow of fuel to said pulse detonation combustor is regulated based on pressure within said pulse detonation combustor.

32. The method of claim 31, wherein a rate or pressure of said flow of fuel is controlled by at least one flow control device.

33. The method of claim 31, wherein said flow of oxidizer is regulated with pressure within said pulse detonation combustor.

34. The method of claim 31, wherein said flow of oxidizer is controlled by at least one flow control device.

35. The method of claim 31, further comprising changing at least one of said flow of oxidizer, said flow of fuel, and an ignition frequency of said ignition source based on a change in an operating condition of said pulse detonation combustor.

36. The method of claim 31, wherein said flow of oxidizer is controlled by a valve.

37. The method of claim 31, further comprising starting and stopping said fuel flow to said pulse detonation combustor using pressure within said pulse detonation combustor.

38. The method of claim 31, further comprising causing said fuel to enter said combustor after said oxidizer enters said combustor.