Serial rotating detonation combustor systems

Patent metadata

Field	Value
Publication number	US-12352224-B2
Application number	US-202318377151-A
Country	US
Kind code	B2
Filing date	Oct 5, 2023
Priority date	Oct 5, 2023
Publication date	Jul 8, 2025
Grant date	Jul 8, 2025

Abstract

Combustor systems are provided that include rotating detonation combustors (RDCs) arranged in series. In some embodiments, a combustor system includes a volume that receives a core oxidizer-fuel mixture. The combustor system includes a first RDC having a first detonation chamber. The first detonation chamber receives a first pilot oxidizer-fuel mixture and is bounded by a first channel formed in a peripheral wall. The combustor system further includes at least one additional RDC having a second detonation chamber. The second detonation chamber receives a second pilot oxidizer-fuel mixture and is bounded by a second channel formed in the peripheral wall. The first pilot oxidizer-fuel mixture reacts in the first detonation chamber and the second pilot oxidizer-fuel mixture reacts in the second detonation chamber to generate rotating detonation combustion waves that are guided by the first channel and the second channel to support a reaction that consumes the core oxidizer-fuel mixture.

First claim

What is claimed is:

1. A combustor system comprising:
a first wall defining at least in part a core that receives a core oxidizer-fuel mixture, the core including a first detonation chamber and at least one additional detonation chamber, the first wall including a first outer channel that extends circumferentially about the first detonation chamber and at least one additional outer channel that extends circumferentially about the at least one additional detonation chamber, wherein the first wall is common outer wall that directly borders the first detonation chamber and the at least one additional detonation chamber; and
at least one outer pilot oxidizer-fuel supply system that supplies a pilot oxidizer-fuel mixture to the first outer channel and the at least one additional outer channel;
wherein the pilot oxidizer-fuel mixture is configured to ignite to generate rotating detonation waves that are guided by the first outer channel and the at least one additional outer channel to support a reaction that consumes the core oxidizer-fuel mixture.

2. The combustor system of claim 1 , wherein the first wall includes a first backward-facing step and a first forward-facing step that are recessed in the first wall, the first backward-facing step and the first forward-facing step joined together by a first recessed surface, and wherein the first backward-facing step, the first forward-facing step, and the first recessed surface define the first outer channel.

3. The combustor system of claim 2 , wherein the first wall includes a second backward-facing step and a second forward-facing step that are recessed in the first wall, the second backward-facing step and the second forward-facing step joined together by a second recessed surface, and wherein the second backward-facing step, the second forward-facing step, and the second recessed surface define the at least one additional outer channel.

4. The combustor system of claim 1 , further including a centerbody bounded by an external surface, wherein the external surface of the centerbody includes a first inner channel and at least one additional inner channel formed therein.

5. The combustor system of claim 4 , wherein the centerbody further includes:
at least one inner pilot fuel supply system that supplies at least one inner pilot oxidizer-fuel mixture to the first inner channel and the at least one additional inner channel.

6. The combustor system of claim 4 , wherein the first inner channel and the first outer channel are disposed at the same position along a length of the combustor system, and wherein the at least one additional inner channel and the at least one additional outer channel are disposed at the same position along the length of the combustor system.

7. The combustor system of claim 4 , wherein the first inner channel is staggered from the first outer channel along a length of the combustor system, and wherein the at least one additional inner channel is staggered from the at least one additional outer channel along the length of the combustor system.

8. The combustor system of claim 4 , wherein the external surface of the centerbody includes a first backward-facing step and a first recessed surface that are recessed in the external surface, and wherein the first backward-facing step and the first recessed surface define the first inner channel.

9. The combustor system of claim 8 , wherein the external surface of the centerbody includes a second backward-facing step and a second recessed surface that are recessed in the external surface, and wherein the second backward-facing step and the second recessed surface define the at least one additional inner channel.

10. The combustor system of claim 1 , wherein at least a portion of the core includes a movable centerbody.

11. The combustor system of claim 1 , wherein at least one of the first detonation chamber or the at least one additional detonation chamber is void of a centerbody.

12. The combustor system of claim 1 , wherein at least one of the first detonation chamber or the at least one additional detonation chamber includes a centerbody.

13. The combustor system of claim 11 , wherein the centerbody has a tapered shape that increases in size from upstream to downstream.

14. The combustor system of claim 1 , wherein the combustor system is configured for utilization in at least one of a ramjet engine, a scramjet engine, a gas turbine engine, or a rocket engine.

15. The combustor system of claim 1 , wherein at least a portion of the first wall has a thickness with a taper that decreases in size from upstream to downstream.

16. The combustor system of claim 1 , wherein the first detonation chamber has a first cross-sectional area and the at least one additional detonation chamber has a second cross-sectional area, the second cross-sectional area being different than the first cross-sectional area.

17. A method comprising:
supplying a core oxidizer-fuel mixture to a combustor system including a first rotating detonation combustor and at least one additional rotating detonation combustor arranged in series, the first rotating detonation combustor and the second rotating detonation combustor bordered directly by common outer wall;
supplying a first pilot oxidizer-fuel mixture to the first rotating detonation combustor;
supplying a second pilot oxidizer-fuel mixture to the at least one additional rotating detonation combustor; and
igniting at least one of the first pilot oxidizer-fuel mixture in the first rotating detonation combustor or the second pilot oxidizer-fuel mixture in the at least one additional rotating detonation combustor to generate rotating detonation waves that consume at least a portion of the core oxidizer-fuel mixture.

18. The method of claim 17 , further comprising stabilizing the rotating detonation waves via a first channel in the first rotating detonation combustor and a second channel in the at least one additional rotating detonation combustor.

19. A combustor system comprising:
a first wall defining at least in part a core that receives a core oxidizer-fuel mixture, the core including a first detonation chamber and at least one additional detonation chamber, wherein the first wall is common outer wall that directly borders the first detonation chamber and the at least one additional detonation chamber;
a centerbody disposed in the core, the centerbody having an external surface including a first inner channel that extends circumferentially about the first detonation chamber and at least one additional inner channel that extends circumferentially about the at least one additional detonation chamber; and
at least one inner pilot oxidizer-fuel supply system that supplies a pilot oxidizer-fuel mixture to the first inner channel and the at least one additional inner channel;
wherein the pilot oxidizer-fuel mixture ignites to generate rotating detonation waves that are guided by the first inner channel and the at least one additional inner channel to support a reaction that consumes the core oxidizer-fuel mixture.

20. The combustor system of claim 19 , wherein the external surface of the centerbody includes a first backward-facing step and a first recessed surface that are recessed in the external surface, and wherein the first backward-facing step and the first recessed surface define the first inner channel; and wherein the external surface of the centerbody includes a second backward-facing step and a second recessed surface that are recessed in the external surface, and wherein the second back

Assignees

• Gen Electric

Inventors

• Singh Kapil
• Depperschmidt Daniel
• Cross Arin Elspeth Lastufka
• Monahan Sarah M

Classifications

• F02C5/02

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

• F02C5/00

  Gas-turbine plants characterised by the working fluid being generated by intermittent combustion · CPC title

• F23R7/00

  Intermittent or explosive combustion chambers · CPC title

• F02K9/605

  Reservoirs · CPC title

• F02K9/52

  Injectors · CPC title