Combustor acoustic damping structure

1. A combustor assembly for a gas turbine engine, the combustor assembly comprising:

an annular bulkhead adjacent to a diffuser cavity;

a deflector downstream of the annular bulkhead and adjacent to a combustion chamber;

a bulkhead support coupled to an upstream side of the deflector, wherein the deflector and the bulkhead support together define a bulkhead conduit therethrough to the combustion chamber;

a first walled enclosure comprising a first wall coupled to the bulkhead support, wherein the first walled enclosure defines a first cavity and a hot side orifice, wherein the hot side orifice is adjacent to and in fluid communication with the bulkhead conduit; and

a second walled enclosure that comprises a second wall that is not part of the first walled enclosure, that is coupled to the first walled enclosure, and that defines a second cavity and a second opening adjacent to the diffuser cavity,

wherein the second walled enclosure further defines a second cold side walled tube extended into the diffuser cavity from the second cavity, and

wherein the second cold side walled tube is the only opening of the second walled enclosure.

2. The combustor assembly of claim 1 , wherein the bulkhead support comprises a cavity wall extended toward the deflector, and wherein the cavity wall defines the bulkhead conduit between the cavity wall, the bulkhead support, and the deflector.

3. The combustor assembly of claim 1 , wherein the first walled enclosure further defines a cold side orifice adjacent to and in fluid communication with the diffuser cavity.

4. The combustor assembly of claim 3 , wherein the first walled enclosure further defines a first cold side walled tube extended into the diffuser cavity from the first cavity.

5. The combustor assembly of claim 1 , wherein the first walled enclosure defines a volume of the first cavity and the bulkhead conduit, and a length of the first cold side walled tube versus a diameter of the cold side orifice, each configured to attenuate pressure oscillations at one or more frequencies.

6. The combustor assembly of claim 1 , wherein the bulkhead conduit defines a substantially cylindrical bore extended through the deflector and the bulkhead support.

7. The combustor assembly of claim 1 , further comprising:

a mount member coupling the first walled enclosure and the second walled enclosure to the annular bulkhead of the combustor.

8. The combustor assembly of claim 7 , wherein the mount member defines a mechanical fastener.

9. The combustor assembly of claim 5 , wherein the second walled enclosure defines a volume of the second cavity, and a length of the second cold side walled tube versus a diameter of a second orifice, each configured to attenuate pressure oscillations at one or more frequencies.

10. A gas turbine engine, the gas turbine engine comprising:

a combustor assembly comprising:

an annular bulkhead adjacent to a diffuser cavity and upstream of an annular dome assembly adjacent to a combustion chamber;

a damper comprising:

a first walled enclosure that comprises a first wall coupled to the annular dome assembly, and

a second walled enclosure that comprises a second wall that is not part of the first walled enclosure and that is coupled to the first walled enclosure,

wherein the first walled enclosure defines a first cavity and a hot side orifice adjacent to the combustion chamber,

wherein the second walled enclosure defines a second cavity and a second opening adjacent to the diffuser cavity,

wherein the damper is disposed between the annular bulkhead and the annular dome assembly of the combustor assembly,

wherein the first walled enclosure of the damper further comprises a first walled tube extended from the first cavity through the annular dome assembly, and wherein the first walled tube defines a first opening adjacent to the combustion chamber and in fluid communication with the first cavity, and

wherein the annular dome assembly defines a gap between the first walled tube and the deflector through which a portion of air flows from the diffuser cavity to the combustion chamber.

11. The gas turbine engine of claim 10 , wherein the first walled enclosure of the damper defines a volume of the first cavity, and a length of a first cold side walled tube versus a diameter of a cold side orifice, each configured to attenuate pressure oscillations at one or more frequencies.

12. A gas turbine engine, the gas turbine engine comprising:

a combustor assembly comprising:

an annular bulkhead adjacent to a diffuser cavity and upstream of an annular dome assembly adjacent to a combustion chamber;

a damper comprising:

a first walled enclosure that comprises a first wall coupled to the annular dome assembly, and

a second walled enclosure that comprises a second wall that is not part of the first walled enclosure and that is coupled to the first walled enclosure,

wherein the first walled enclosure defines a first cavity and a hot side orifice adjacent to the combustion chamber,

wherein the second walled enclosure defines a second cavity and a second opening adjacent to the diffuser cavity, and

wherein the damper is disposed between the annular bulkhead and the annular dome assembly of the combustor assembly,

wherein the second cold side walled tube is the only opening of the second walled enclosure, and

wherein the second walled enclosure of the damper further comprises a second cold side walled tube extended into the second cavity and/or the diffuser cavity.

13. The gas turbine engine of claim 12 , wherein the first walled enclosure of the damper further comprises a first walled tube extended from the first cavity through the annular dome assembly, and wherein the first walled tube defines a first opening adjacent to the combustion chamber and in fluid communication with the first cavity.

14. The gas turbine engine of claim 12 , wherein the damper further comprises a mount member extended through and coupled to the annular bulkhead, and wherein the mount member is coupled to the first walled enclosure and the second walled enclosure.

15. The gas turbine engine of claim 12 , wherein the damper is disposed along a radial direction between a swirler and the annular bulkhead.

16. The gas turbine engine of claim 12 , wherein the second walled enclosure of the damper defines a volume of the second cavity, and a length of the second cold side walled tube versus a diameter of a second orifice, each configured to attenuate pressure oscillations at one or more frequencies.

17. The gas turbine engine of claim 12 , wherein the first walled enclosure of the damper further defines a cold side orifice adjacent to and in fluid communication with the diffuser cavity.

18. The gas turbine engine of claim 17 , wherein the first walled enclosure of the damper further comprises a first cold side walled tube extended from the first walled enclosure to the diffuser cavity, and wherein the cold side orifice is defined at the first cold side walled tube adjacent to the diffuser cavity.