Tuned cavity rotating detonation combustion system

Patent metadata

Field	Value
Publication number	US-9732670-B2
Application number	US-201314103928-A
Country	US
Kind code	B2
Filing date	Dec 12, 2013
Priority date	Dec 12, 2013
Publication date	Aug 15, 2017
Grant date	Aug 15, 2017

Abstract

A tuned cavity rotating detonation combustion system includes a an annular chamber having an inlet and an outlet; a valve plate at the inlet of the annular chamber and comprising a plurality of openings spaced circumferentially around the inlet; a plurality of tubes each having an open end in communication with a corresponding opening of the valve plate and a closed end forming a tuned cavity, and a first opening between the open end and the closed end for injection of air; and a plurality of fuel injectors corresponding to the plurality of tubes, each fuel injector being configured to inject fuel into the tube between the first opening and the open end. Each of the tuned cavities has a length sized to resonate at a same frequency as a continuous detonation frequency of at least one detonation wave in the annular chamber. Alternately, or additionally, a plurality of flame arresters corresponding to the plurality of tubes are configured to arrest the at least one detonation wave generated in the detonation chamber from travelling into the tube.

First claim

The invention claimed is:

1. A rotating detonation combustion system, comprising:
an annular detonation chamber having an inner wall, an outer wall, an inlet and an outlet;
a valve plate at the inlet of the annular detonation chamber and comprising a plurality of openings spaced around the inlet;
a plurality of tubes each having an open end in communication with a corresponding opening of the valve plate and a closed end forming a tuned cavity, and a first opening between the open end and the dosed end for injection of air; and
a plurality of fuel injectors corresponding to the plurality of tubes, each fuel injector being configured to inject fuel into corresponding one of the plurality of tubes between the first opening and the open end to form a fuel/air mixture, wherein each of the tuned cavities has a length sized to resonate at a same frequency as an effective continuous detonation frequency of at least one detonation wave in the annular detonation chamber,
wherein the closed end of each of the plurality of tubes comprises a piston configured to adjust the length of the tuned cavity; and
wherein a controller is configured to control a position of the piston to change the length of the tuned cavity to match the detonation frequency as a fuel/air mixture temperature at the inlet changes.

2. A rotating detonation combustion system according to claim 1 , further comprising:
a controller configured to control the fuel injectors to inject fuel into the tubes in a phased relationship of the at least one detonation wave in the annular detonation chamber.

3. The rotating detonation combustion system according to claim 2 , wherein the controller turns on the fuel injectors in a pattern that rotates in synchronization with the at least one detonation wave with a phase lag.

4. The rotating detonation combustion system according to claim 3 , wherein the phase lag is configured to allow the fuel/air mixture to propagate into the annular detonation chamber.

5. The rotating detonation combustion system according to claim 3 , wherein the controller turns off the fuel injectors upstream of the detonation wave to prevent the flame from prorogating into corresponding one of the plurality of tubes.

6. The rotating detonation combustion system according to claim 1 , wherein the length of each of the tuned cavities is configured to return a pressure wave in corresponding one of the plurality of tubes in phase with the at least one detonation wave to reduce ingestion of burnt fuel/air mixture into the tubes.

7. The rotating detonation combustion system according to claim 1 , further comprising:
an igniter configured to ignite the fuel/air mixture.

8. The rotating detonation combustion system according to claim 1 , wherein the first opening of each tube is generally positioned at a pressure antinode of a static pressure wave in each one of the plurality of tubes.

9. The rotating detonation combustion system according to claim 1 , wherein the inner wall and the outer wall of the annular detonation chamber are conical.

10. The rotating detonation combustion system according to claim 1 , wherein the inner wall and the outer wall of the annular detonation chamber are curved.

11. The rotating detonation combustion system according to claim 1 , wherein each one of the plurality of tubes has a circular cross section.

12. The rotating detonation combustion system according to claim 1 , wherein each one of the plurality of tubes has a square cross section.

13. The rotating detonation combustion system according to claim 1 , wherein the closed end of each one of the plurality of tubes has a smaller cross section than corresponding one of the plurality of openings in the valve plate.

14. The rotating detonation combustion system according to claim 1 , wherein the closed end of each one of the plurality of tubes has a larger cross section than corresponding one of the plurality of openings in the valve plate.

15. The rotating detonation combustion system according to claim 1 , wherein the openings in the valve plate are circular.

16. The rotating detonation combustion system according to claim 1 , wherein the openings in the valve plate are square.

17. The rotating detonation combustion system according to claim 1 , wherein the fuel injectors are configured to inject fuel flows into the air to create mixtures with an equivalence ratio of between about 0.4 to about 1.4.

18. The rotating detonation combustion system according to claim 3 , wherein the controller controls the fuel injectors to create a fuel-free leading injection region that creates a buffer between a burned filet/air mixture and a fresh fuel/air mixture entering the detonation chamber.

19. A method of combustion, comprising:
introducing a plurality of fuel/air plumes into an annular chamber from a plurality of tubes at in inlet side of the annular chamber, each of the plurality of tubes having an open end at the inlet side and a dosed end opposite the open end forming a tuned cavity;
igniting a fuel/air mixture formed by the plumes to generate at least one detonation wave in the annular chamber, wherein each of the tuned cavities has a length sized to resonate at a same frequency as an effective continuous detonation frequency of the at least one detonation wave in the annular chamber;
adjusting the length of the tuned cavity of each of the plurality of tubes by moving a piston located at the closed end; and
controlling a position of the piston to change the length of the tuned cavity to match the detonation frequency as a fuel/air mixture temperature at the inlet side changes.

20. A method according to claim 19 , further comprising:
controlling a plurality of fuel injectors corresponding to the plurality of tubes to inject fuel into corresponding one of the plurality of tubes in a phased relationship of the at least one detonation wave in the annular chamber.

21. A method according to claim 20 , wherein controlling the plurality of fuel injectors comprises turning on the fuel injectors in a pattern that rotates in synchronization with the at least one detonation wave with a phase lag.

22. A method according to claim 21 , wherein the phase lag is configured to allow the fuel/air mixture to propagate into the annular chamber.

23. A method according to claim 21 , further comprising:
turning off the fuel injectors upstream of the at least one detonation wave to prevent the flame from propagating into the tubes.

24. A method according to claim 19 , further comprising:
returning a pressure wave in the plurality of tubes in phase with the at least one detonation wave to reduce ingestion of burnt fuel/air mixture into corresponding one of the plurality of tubes.

25. A method according to claim 19 , further comprising:
injecting air into each of the plurality of tubes generally at a pressure antinode of a static pressure wave in corresponding one of the plurality of tubes.

26. A method according to claim 25 , wherein the air is injected continuously.

27. A method according to claim 19 , further comprising:
injecting a fuel/air mixture into each of the plurality of tubes generally at a pressure antinode of a static pressure wave in corresponding one of the plurality of tubes.

28. A method according to claim 27 , wherein the fuel/air mixture is lean.

29. A method according to claim 19 , further

Assignees

• Gen Electric

Inventors

• Joshi Narendra Digamber
• Idelchik Michael Solomon

Classifications

• F02B53/04 Primary

  Charge admission or combustion-gas discharge · CPC title

• F02C5/02

  characterised by the arrangement of the combustion chamber in the chamber in the plant (combustion chambers per se F23R) · CPC title

• F23R3/14

  by using swirl vanes · CPC title

• F23R7/00 Primary

  Intermittent or explosive combustion chambers · CPC title