THRUST MODULATION IN A MULTIPLE COMBUSTOR PULSE DETONATION ENGINE USING CROSS-COMBUSTOR DETONATION INITIATION

• US 20110126511A1
• Filed: 11/30/2009
• Published: 06/02/2011
• Est. Priority Date: 11/30/2009
• Status: Abandoned Application

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Glaser, Aaron Jerome, Rasheed, Adam, Joshi, Narendra Digamber, Hofer, Douglas Carl
• Application Number:
  US12/627,763
• Publication Number:
  US 20110126511A1
• Time in Patent Office: Days
• US Class Current: 60/248
• CPC Class Codes: F02C 5/00 Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
• CPC Class Codes: F05D 2270/051 Thrust

Abstract

A method and apparatus for modulating the thrust during a flight envelope of a multiple combustor chamber detonation engine using cross-combustor chamber detonation initiation are provided. The detonation combustor chambers are filled with a combustible mixture of fuel and oxidizer. The combustible mixture in one of the detonation combustor chambers is ignited by an ignition source, and the remaining detonation combustor chambers are ignited by detonation cross-firing via connectors. A controller controls the ignition source and the supply of oxidizer and fuel to the detonation combustor chambers to modulate the thrust of the engine during the flight envelope.

Claims

1. An engine, comprising:

a plurality of detonation combustor chambers, at least one of the pulse detonation combustor chambers comprising an ignition source;

a plurality of connectors, each of the connectors connecting two of the detonation combustor chambers to facilitate cross-fire detonation between the two pulse detonation combustor chambers;

an oxidizer supply coupled to the detonation combustor chambers;

a fuel supply coupled to the detonation combustor chambers; and

a controller to control the supply of oxidizer and fuel from the oxidizer supply and the fuel supply to the detonation combustor chambers to modulate the thrust of the engine during the flight envelope.

2. The engine of claim 1, further comprising:

one or more variable geometry exit nozzles coupled to one or more of the detonation combustor chambers; and

wherein the controller controls the variable geometry exit nozzles to modulate the thrust of the engine during the flight envelope.

3. The engine of claim 1, wherein the connectors are variable length connectors;

and wherein the controller controls the length of the variable length connectors to modulate the thrust of the engine during the flight envelope.

4. The engine of claim 1, wherein the oxidizer supply comprises inlet valves coupled to the pulse detonation combustor chambers, respectively.

5. The engine of claim 1, wherein the oxidizer supply comprises one or more inlet valves coupled to one or more pulse detonation combustor chambers.

6. The engine of claim 1, wherein the controller controls ignition of the ignition source to vary a frequency of firing the pulse detonation combustor chambers.

7. The engine of claim 1, wherein the controller controls the supply of fuel to vary a firing pattern of one or more of the pulse detonation combustor chambers.

8. The engine of claim 1, wherein the controller controls the supply of the fuel and the supply of the oxidizer to vary one of an equivalence ratio or a fill fraction of one or more of the pulse detonation combustor chambers.

9. The engine of claim 8, wherein the controller controls the supply of the oxidizer and the fuel for one or more of the pulse detonation combustor chambers to fill the associated pulse detonation combustor chamber with the oxidizer and the fuel to obtain the equivalence ratio less than one to reduce the thrust of the engine during the flight envelope.

10. The engine of claim 8, wherein controller controls the supply of the oxidizer and the fuel for one or more of the pulse detonation combustor chambers to fill the associated pulse detonation combustor chamber with the oxidizer and the fuel to obtain the fill fraction less than one to reduce the thrust of the engine during the flight envelope.

11. The engine of claim 8, wherein the controller controls the supply of the oxidizer and the fuel for one or more of the pulse detonation combustor chambers wherein the equivalence ratio is varied along a length of the one or more pulse detonation combustor chambers.

12. The engine of claim 1, wherein the engine is a pulse detonation turbine engine.

13. A method for thrust modulation during a flight envelope in an engine having detonation combustor chambers coupled together by connectors, the method comprising:

filling the detonation combustor chambers with a combustible mixture of oxidizer and fuel;

igniting the combustible mixture in one of the detonation combustor chambers via an ignition source to generate a detonation shock wave that propagates in the one detonation combustor chamber;

igniting remaining detonation combustor chambers by propagating the detonation shock wave from the one detonation combustor chamber to the remaining detonation combustor chambers via the connectors; and

controlling supply of the oxidizer and the fuel to the detonation combustor chambers to modulate the thrust of the engine during the flight envelope.

14. The method of claim 13, wherein the controlling the supply of the oxidizer and the fuel comprises:

controlling ignition of the ignition source to vary a frequency of firing the detonation combustor chambers.

15. The method of claim 13, wherein the controlling the supply of the oxidizer and the fuel comprises:

controlling at least one of the supply of the oxidizer or the fuel to vary a firing pattern of the detonation combustor chambers.

16. The method of claim 13, wherein the controlling the supply of the oxidizer and the fuel comprises:

controlling the supply of the fuel for one or more of the detonation combustor chambers to prevent fuel supply for a predetermined period of time during a firing pattern cycle.

17. The method of claim 13, wherein the controlling the supply of the oxidizer and the fuel comprises:

controlling the supply of the oxidizer and the fuel to vary an equivalence ratio of one or more of the detonation combustor chambers during a firing pattern cycle.

18. The method of claim 17, wherein the controlling the supply of the oxidizer and the fuel comprises:

supplying the fuel for one or more of the detonation combustor chambers during a firing pattern cycle for a period of time to fill the associated detonation combustor chamber with fuel to obtain an equivalence ratio less than one to reduce the thrust of the engine during the flight envelope.

19. The method of claim 13, wherein controlling the ns comprises:

controlling the supply of the oxidizer and the fuel to vary a fill fraction of one or more of the detonation combustor chambers.

20. The method of claim 19, wherein the controlling the supply of the oxidizer and the fuel comprises:

supplying the oxidizer and the fuel for one or more of the detonation combustor chambers during a firing pattern cycle for a period of time to fill the associated detonation combustor chamber to obtain a fill fraction less than one to reduce the thrust of the engine during the flight envelope.

21. The method of claim 13, wherein the detonation combustor chambers comprise variable geometry exit nozzles, respectively, and wherein the method further comprises controlling the variable geometry exit nozzles for one or more of the detonation combustor chambers to adjust an opening of the variable geometry exit nozzles to modulate the thrust from the engine during the flight envelope.

22. The method of claim 13, wherein the connectors are variable length connectors, and wherein the method further comprises controlling the length one or more of the variable length connectors to modulate the thrust from the engine during the flight envelope.

23. A computer-readable medium comprising computer-readable instructions of a computer program that, when executed by a processor, cause the processor to perform a method for thrust modulation during a flight envelope in an engine having detonation combustor chambers coupled together by connectors, the method comprising:

filling the detonation combustor chambers with a combustible mixture of oxidizer and fuel;

igniting the combustible mixture in one of the detonation combustor chambers via an ignition source to generate a detonation shock wave that propagates in the one detonation combustor chamber;

igniting remaining detonation combustor chambers by propagating the detonation shock wave from the one detonation combustor chamber to the remaining detonation combustor chambers via the connectors; and

controlling supply of the oxidizer and the fuel to the detonation combustor chambers to modulate the thrust of the engine during the flight envelope.

24. The computer-readable medium of claim 23, wherein the controlling the supply of the oxidizer and the fuel comprises:

controlling ignition of the ignition source to vary a frequency of firing the detonation combustor chambers.

25. The computer-readable medium of claim 23, wherein the controlling the supply of the oxidizer and the fuel comprises:

controlling the supply of at least one of the oxidizer and the fuel to vary a firing frequency of the detonation combustor chambers.

26. The computer-readable medium of claim 23, wherein the controlling the supply of the oxidizer and the fuel comprises:

controlling the supply of the fuel for one or more of the detonation combustor chambers to prevent fuel flow for a predetermined period of time during a firing pattern cycle of the detonation combustor chambers.

27. The computer-readable medium of claim 23, wherein the controlling the supply of the oxidizer and the fuel comprises:

controlling the supply of the oxidizer and the fuel to vary an equivalence ratio of one or more of the detonation combustor chambers during a firing pattern cycle.

28. The computer-readable medium of claim 23, wherein the controlling the supply of the oxidizer and the fuel comprises:

controlling the supply of the oxidizer and the fuel to vary a fill fraction of one or more of the detonation combustor chambers during a firing pattern cycle.

29. The computer-readable medium of claim 23, wherein the detonation combustor chambers comprise one or more variable geometry exit nozzles, wherein the controlling the supply of the oxidizer and the fuel comprises controlling the variable geometry exit nozzles of one or more of the detonation combustor chambers to modulate the thrust from the engine during the flight envelope.

30. The computer-readable medium of claim 23, wherein the connectors are variable length connectors, and wherein the controlling the supply of the oxidizer and the fuel comprises controlling the length of the variable length connectors of one or more of the detonation combustor chambers to modulate the thrust from the engine during the flight envelope.