# US 10,480,414 B2 · Combustor and gas turbine with phase adjusting units in the fuel nozzles

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- Number: US 10,480,414 B2
- Document ID: US10480414B2
- Status: Granted
- Kind: B2
- Application number: 14/777,060
- Filed: 2014-02-14
- Published: 2016-02-04
- Granted: 2019-11-19
- Earliest claimed: 2013-03-22
- Assignees: Mitsubishi Heavy Industries, Ltd.
- Applicants: Mitsubishi Heavy Industries, Ltd.
- Inventors: Mitsunori Isono; Toshihiko Saito; Kotaro Miyauchi
- Web page: https://patentgrep.com/patent/US10480414B2

## CPC

- F02C 7/222: {Fuel flow conduits, e.g. manifolds}
- F23M 20/005: {Noise absorbing means}
- F23R 3/14: by using swirl vanes
- F23R 3/286: {having fuel-air premixing devices (F23R3/30 takes precedence)}
- F23R 3/343: {Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion (ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00)}
- F23R 3/46: Combustion chambers comprising an annular arrangement of {several essentially tubular} flame tubes within a common annular casing or within individual casings
- F05D 2260/96: Preventing, counteracting or reducing vibration or noise
- F05D 2260/963: by Helmholtz resonators
- F05D 2270/333: Noise or sound levels
- F23D 2210/00: Noise abatement
- 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)
- F23M: CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- 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
- F23D: BURNERS

## Abstract

A combustor includes fuel nozzles that extend in an axial direction of a combustor main body and are capable of injecting fuel from injection holes on a combustion chamber side. The combustor includes a phase adjusting unit which partially changes a flow path cross-sectional area of at least one of the fuel nozzles in the axial direction such that phases of flow rate fluctuation of fuel do not match with respect to at least two of the fuel nozzles.

## Claims

### Claim 1

A combustor comprising:
a plurality of main fuel nozzles extending in an axial direction of a combustor main body, each of the plurality of main fuel nozzles having a plurality of injection holes and being capable of injecting fuel from the plurality of injection holes therein on a combustion chamber side,
a plurality of phase adjusting units, each configured to partially change a flow path cross-sectional area of a respective one of at least two adjacent main fuel nozzles of the plurality of main fuel nozzles such that phases of flow rate fluctuation of the fuel in the at least two adjacent main fuel nozzles do not match, and
a manifold,
wherein the plurality of main fuel nozzles branch from and are connected to the manifold,
wherein each of the plurality of phase adjusting units is shifted away from an adjacent phase adjusting unit of the plurality of phase adjusting units in the axial direction,
wherein the plurality of main fuel nozzles are annularly spaced apart from each other in a circumferential direction,
wherein the plurality of phase adjusting units are between the manifold and the pluralities of injection holes of the at least two adjacent main fuel nozzles of the plurality of fuel nozzles,
wherein the respective plurality of injection holes of each of the at least two adjacent main fuel nozzles are larger than the respective plurality of injection holes of the remaining main fuel nozzles of the plurality of main fuel nozzles, and
wherein each respective plurality of injection holes of each of the at least two adjacent main fuel nozzles is increased in size corresponding to a respective increase in magnitude of pressure loss occurring across each respective phase adjusting unit.

### Claim 2

A combustor comprising:
a plurality of main fuel nozzles extending in an axial direction of a combustor main body, each of the plurality of main fuel nozzles having a plurality of injection holes and being capable of injecting fuel from the plurality of injection holes therein on a combustion chamber side,
a plurality of phase adjusting units, each configured to partially change a flow path cross-sectional area of a respective one of at least two adjacent main fuel nozzles of the plurality of main fuel nozzles such that phases of flow rate fluctuation of the fuel in the at least two adjacent main fuel nozzles do not match, and
a casing,
wherein each of the plurality of phase adjusting units is shifted away from an adjacent phase adjusting unit of the plurality of phase adjusting units in the axial direction,
wherein the plurality of main fuel nozzles are annularly spaced apart from each other in a circumferential direction,
wherein the number of phase adjusting units of the plurality of phase adjusting units is equal to the number of main fuel nozzles of the plurality of main fuel nozzles such that each of the plurality of main fuel nozzles corresponds to one of the plurality of phase adjusting units,
wherein the casing has a rear wall,
wherein the plurality of phase adjusting units are between the rear wall of the casing and the pluralities of injection holes,
wherein the respective plurality of injection holes of at least one of the plurality of main fuel nozzles is larger than the respective plurality of injection holes of an adjacent one of the plurality of main fuel nozzles, and
wherein each respective plurality of injection holes of each of the plurality of main fuel nozzles is increased in size corresponding to a respective increase in magnitude of pressure loss occurring across each respective phase adjusting unit.

### Claim 3 (depends on 1)

The combustor according to claim 1, wherein: the plurality of main fuel nozzles are in a row, and every other main fuel nozzle of the plurality of main fuel nozzles corresponds to one of the plurality of phase adjusting units in an array direction in the plurality of main fuel nozzles.

### Claim 4 (depends on 1)

The combustor according to claim 1, wherein: for each of the plurality of main fuel nozzles having a respective one of the plurality of phase adjusting units, a flow path cross-sectional area from the respective one of the plurality of phase adjusting units to the respective plurality of injection holes in the axial direction is constant, and the flow path cross-sectional areas of the plurality of main fuel nozzles between the respective plurality of phase adjusting units and the respective pluralities of injection holes in the axial direction are identical.

### Claim 5 (depends on 1)

The combustor according to claim 1, wherein the plurality of phase adjusting units are configured to make the phases of flow rate fluctuation of the fuel in the at least two adjacent main fuel nozzles have opposite phases.

### Claim 6 (depends on 1)

The combustor according to claim 1, wherein each of the plurality of phase adjusting units has a cavity portion configured to increase a flow path cross-sectional area of a respective one of the plurality of main fuel nozzles.

### Claim 7 (depends on 1)

The combustor according to claim 1, wherein each of the plurality of phase adjusting units has an orifice portion configured to reduce a flow path cross-sectional area of a respective one of the plurality of main fuel nozzles.

### Claim 8 (depends on 1)

The combustor according to claim 1, wherein each of the plurality of phase adjusting units is made of a porous material including pores in a flow path of a respective one of the plurality of main fuel nozzles.

### Claim 9 (depends on 1)

A gas turbine comprising the combustor according to claim 1.

### Claim 10 (depends on 1)

The combustor according to claim 1, wherein the plurality of phase adjusting units are not valves.

### Claim 11 (depends on 2)

The combustor according to claim 2, wherein: the plurality of main fuel nozzles are in a row, and every other main fuel nozzle of the plurality of main fuel nozzles corresponds to one of the plurality of phase adjusting units in an array direction in the plurality of main fuel nozzles.

### Claim 12 (depends on 2)

The combustor according to claim 2, wherein: for each of the plurality of main fuel nozzles having a respective one of the plurality of phase adjusting units, a flow path cross-sectional area from the respective one of the plurality of phase adjusting units to the respective plurality of injection holes in the axial direction is constant, and the flow path cross-sectional areas of the plurality of main fuel nozzles between the respective plurality of phase adjusting units and the respective pluralities of injection holes in the axial direction are identical.

### Claim 13 (depends on 2)

The combustor according to claim 2, wherein the plurality of phase adjusting units are configured to make the phases of flow rate fluctuation of the fuel in the at least two adjacent main fuel nozzles have opposite phases.

### Claim 14 (depends on 2)

The combustor according to claim 2, wherein each of the plurality of phase adjusting units has a cavity portion configured to increase a flow path cross-sectional area of a respective one of the plurality of main fuel nozzles.

### Claim 15 (depends on 2)

The combustor according to claim 2, wherein each of the plurality of phase adjusting units has an orifice portion configured to reduce a flow path cross-sectional area of a respective one of the plurality of main fuel nozzles.

### Claim 16 (depends on 2)

The combustor according to claim 2, wherein each of the plurality of phase adjusting units is made of a porous material including pores in a flow path of a respective one of the plurality of main fuel nozzles.

### Claim 17 (depends on 2)

A gas turbine comprising the combustor according to claim 2.

### Claim 18 (depends on 2)

The combustor according to claim 2, wherein the plurality of phase adjusting units are not valves.