Granted Patent B1

US 12,366,203 · App. 18/664,924 · Granted Jul 22, 2025

Inventors: Nicholas Arthur Magina (Saratoga Springs, NY); Fei Han (Clifton Park, NY)

Assignee: GENERAL ELECTRIC COMPANY

F02C7/00F05D2260/96F23R2900/00013F23R2900/00014

Abstract

Claims (28)

1. A gas turbine engine comprising:

a compressor section for compressing air flowing therethrough to provide a compressed air flow;

a combustor including a combustion chamber, the combustion chamber configured to combust a mixture of a fuel flow and the compressed air flow to generate combustion products, the combustion products producing an instability in the combustion chamber, the instability having at least one frequency;

a turbine section having at least one turbine driven by the combustion products; and

a multicavity damper in fluid communication with the combustion chamber to damp the instability generated by the combustion products in the combustion chamber, the multicavity damper including:

a bottom surface fluidly connected to the combustion chamber;

a top surface opposite the bottom surface;

a cylindrical surface extending from the bottom surface to the top surface in an axial direction, the bottom surface, the top surface, and the cylindrical surface defining a main damper cavity;

a first inner wall positioned in the main damper cavity extending in the axial direction from the bottom surface, the top surface, or both the bottom surface and the top surface; and

a second inner wall positioned in the main damper cavity between the bottom surface and the top surface, and extending from the first inner wall to the cylindrical surface, the first inner wall and the second inner wall dividing the main damper cavity into a plurality of differing cavity volumes, each differing cavity volume having a unique length to target a unique instability frequency.

2. The gas turbine engine of claim 1 , wherein each of the plurality of cavity volumes is fluidly isolated from each other within the multicavity damper.

3. The gas turbine engine of claim 1 , wherein the length of each cavity volume is less than twenty percent different from one another.

4. The gas turbine engine of claim 1 , wherein the length of each cavity volume is greater than twenty percent different from one another.

5. The gas turbine engine of claim 1 , wherein the length of a first cavity volume is less than twenty percent different from a length of a second cavity volume, and the length of the first cavity volume is greater than twenty percent different from a length of a third cavity volume.

6. The gas turbine engine of claim 1 , wherein the length of a first cavity volume is less than twenty percent different from a length of a second cavity volume, and the length of the second cavity volume is greater than twenty percent different from a length of a third cavity volume.

7. The gas turbine engine of claim 1 , wherein a number of cavity volumes of the multicavity damper is directly proportional to a number of target frequencies.

8. The gas turbine engine of claim 1 , wherein the multicavity damper is coupled to an outer liner of the combustor through a single opening in the outer liner.

9. The gas turbine engine of claim 8 , wherein the multicavity damper is one of a plurality of multicavity dampers disposed circumferentially about the combustor.

10. The gas turbine engine of claim 1 , wherein the plurality of cavity volumes comprises a first cavity volume having a first cavity volume length and a second cavity volume having a second cavity volume length.

11. The gas turbine engine of claim 10 , wherein the first cavity volume damps a first target frequency and the second cavity volume damps a second target frequency, wherein the first target frequency is different than the second target frequency.

12. The gas turbine engine of claim 11 , wherein the first cavity volume length is less than twenty percent different than the second cavity volume length such that an attenuation curve of the multicavity damper comprises two frequency curves with distinct frequency peaks, the two frequency curves merging to provide a broadened damping frequency band.

13. The gas turbine engine of claim 11 , wherein the first cavity volume length is greater than twenty percent different than the second cavity volume length such that an attenuation curve of the multicavity damper comprises two frequency curves with distinct frequency peaks, the two frequency curves being distinct and separate with no blending of the frequency curves.

14. The gas turbine engine of claim 11 , further comprising a third cavity volume having a third cavity volume length, wherein the third cavity volume damps a third target frequency that is different from the first target frequency and the second target frequency.

15. The gas turbine engine of claim 1 , wherein a first cavity volume has a length that is less than a length of the main damper cavity and a second cavity volume has a length that is greater than a length of the main damper cavity.

16. The gas turbine engine of claim 1 , further comprising a third inner wall extending parallel to the first inner wall and a fourth inner wall extending parallel to the second inner wall, wherein the main damper cavity comprises a third cavity volume defined between each of the first inner wall, the second inner wall, the third inner wall, and the fourth inner wall.

17. The gas turbine engine of claim 1 , further comprising at least one opening arranged on the bottom surface to fluidly connect the at least one of the plurality of cavity volumes to the combustion chamber.

18. The gas turbine engine of claim 1 , further comprising at least one opening arranged on the cylindrical surface to fluidly connect the at least one of the plurality of cavity volumes to an outer passage of the combustor.

19. The gas turbine engine of claim 1 , further comprising a first damper body portion and a second damper body portion capable of being fastened together to form a body of the multicavity damper.

Assignments (1)

References Cited (28)