# US 2025/0354516 A1 · Turbine engine having a multicavity damper

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- Number: US 2025/0354516 A1
- Document ID: US20250354516A1
- Status: Published application
- Kind: A1
- Application number: 19/273,788
- Filed: 2025-07-18
- Published: 2025-11-20
- Earliest claimed: 2024-05-15
- Assignees: General Electric Company
- Applicants: General Electric Company
- Inventors: Nicholas Arthur Magina; Fei Han
- Web page: https://patentgrep.com/patent/US20250354516A1

## CPC

- F02C 7/00: Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00)
- F23R 3/005: {Combined with pressure or heat exchangers}
- F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)}
- F05D 2260/96: Preventing, counteracting or reducing vibration or noise
- F23R 2900/00013: Reducing thermo-acoustic vibrations by active means
- F23R 2900/00014: Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A gas turbine engine includes 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, and a turbine section having at least one turbine driven by the combustion products. The gas turbine engine includes a multicavity damper in fluid communication with the combustion chamber to dampen an instability generated in the combustion chamber by the combustion products. The multicavity damper has a plurality of cavity volumes and the length of each cavity volume is different.

## Claims

### Claim 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 having an axial direction and including:
a bottom surface fluidly connected to the combustion chamber;
a top surface opposite the bottom surface, the top surface having a first top surface and a second top surface, the first top surface located between the second top surface and the bottom surface in the axial direction;
a cylindrical surface extending from the bottom surface to the top surface in the axial direction;
a first inner wall 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 at the first top surface and extending from the first inner wall to the cylindrical surface,
wherein the bottom surface, the cylindrical surface, the first inner wall and the second inner wall define a first cavity volume therebetween, the first cavity volume having a first cavity volume length, and the bottom surface, the second top surface, the cylindrical surface, and the first inner wall define a second cavity volume therebetween, the second cavity volume having a second cavity volume length that is different from the first cavity volume length, wherein the first cavity volume and the second cavity volume together define a main damper cavity.

### Claim 2 (depends on 1)

The gas turbine engine of claim 1, wherein the first cavity volume damps a first target frequency and the second cavity volume damps a second target frequency, the first target frequency being different than the second target frequency.

### Claim 3 (depends on 1)

The gas turbine engine of claim 1, wherein the first cavity volume and the second cavity volume are fluidly isolated from each other within the multicavity damper.

### Claim 4 (depends on 1)

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.

### Claim 5 (depends on 1)

The gas turbine engine of claim 1, wherein the multicavity damper is one of a plurality of multicavity dampers disposed circumferentially about the combustor.

### Claim 6 (depends on 1)

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 first cavity volume or the second cavity volume to the combustion chamber.

### Claim 7 (depends on 1)

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 first cavity volume or the second cavity volume to an outer passage of the combustor.

### Claim 8 (depends on 1)

The gas turbine engine of claim 1, wherein the first cavity volume is defined by a first surface of the first inner wall and the second cavity volume is defined by a second surface of the first inner wall opposite the first surface of the first inner wall.

### Claim 9 (depends on 1)

The gas turbine engine of claim 1, 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.

### Claim 10 (depends on 9)

The gas turbine engine of claim 9, wherein the two frequency curves merge to provide a broadened damping frequency band.

### Claim 11 (depends on 1)

The gas turbine engine of claim 1, 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.

### Claim 12 (depends on 11)

The gas turbine engine of claim 11, wherein the two frequency curves are distinct and separate with no blending of the frequency curves.

### Claim 13 (depends on 1)

The gas turbine engine of claim 1, wherein the multicavity damper has a longitudinal axis and a radial axis and the first inner wall extends parallel to the longitudinal axis.

### Claim 14 (depends on 13)

The gas turbine engine of claim 13, wherein the second inner wall extends parallel to the radial axis perpendicular to the longitudinal axis.

### Claim 15 (depends on 1)

The gas turbine engine of claim 1, further comprising a third inner wall positioned in the main damper cavity extending in the axial direction from one of the bottom surface or the top surface.

### Claim 16 (depends on 15)

The gas turbine engine of claim 15, wherein the first inner wall extends from one of the bottom surface or the top surface and the third inner wall extends from another of the bottom surface or the top surface opposite the first inner wall.

### Claim 17 (depends on 15)

The gas turbine engine of claim 15, wherein the first inner wall and the third inner wall are axially spaced to define a gap between the first inner wall and the third inner wall.

### Claim 18 (depends on 15)

The gas turbine engine of claim 15, wherein the first inner wall and the third inner wall are coplanar.

### Claim 19 (depends on 15)

The gas turbine engine of claim 15, wherein the second cavity volume is defined by the cylindrical surface, the bottom surface, the first inner wall, the third inner wall, and the second top surface.

### Claim 20 (depends on 19)

The gas turbine engine of claim 19, wherein the first cavity volume and the second cavity volume are in fluid communication with each other within the multicavity damper.