# US 12,601,489 B2 · Nozzle assembly, combustor and gas turbine comprising the same

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- Number: US 12,601,489 B2
- Document ID: US12601489B2
- Status: Granted
- Kind: B2
- Application number: 18/402,414
- Filed: 2024-01-02
- Published: 2024-07-04
- Granted: 2026-04-14
- Earliest claimed: 2023-01-02
- Assignees: Doosan Enerbility Co., Ltd.
- Applicants: Doosan Enerbility Co., Ltd.
- Inventors: Borys Shershnyov
- Web page: https://patentgrep.com/patent/US12601489B2

## CPC

- F23R 3/286: {having fuel-air premixing devices (F23R3/30 takes precedence)}
- F02C 7/22: Fuel supply systems
- F23R 3/14: by using swirl vanes
- F05D 2240/35: Combustors or associated equipment
- 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)
- 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)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

Proposed are a nozzle assembly, a combustor using the same, and a gas turbine. The nozzle assembly is configured to inject fuel and compressed air into a combustion chamber of a combustor of a gas turbine, and includes a hollow nozzle frame, a mixture supply tube having a plurality of tubes configured to supply a mixture of air and fuel to the combustion chamber, a fuel supply part configured to supply fuel to the mixture supply tube, an air supply part configured to supply air to the mixture supply tube, and a mixing part including an injection member formed in each of the tubes and configured to inject fuel supplied from the fuel supply part toward air passing through the tube, and a swirl vane formed on one side of the injection member and configured to mix fuel and air passing through the injection member.

## Claims

### Claim 1

A nozzle assembly configured to inject fuel and compressed air into a combustion chamber of a combustor of a gas turbine, the nozzle assembly comprising:
a hollow nozzle frame;
a mixture supply tube having a plurality of tubes configured to supply a mixture of the compressed air and the fuel to the combustion chamber;
a fuel supply part configured to supply the fuel to the mixture supply tube;
an air supply part configured to supply the compressed air to the mixture supply tube; and
a mixing part comprising:
an injection member formed in each of the plurality of tubes and configured to inject the fuel supplied from the fuel supply part into a respective tube of the plurality of tubes and toward the compressed air passing through the respective tube, with the injection member comprising a first hollow tube having a central flow path, through which the fuel and the compressed air flows, formed therein; and
a swirl vane formed on one side of the injection member, with the swirl vane having a flow path formed in a center thereof such that the flow path communicates with the central flow path of the first hollow tube and having blades formed on an outer surface thereof so that the fuel and the compressed air supplied from an outside of the first hollow tube mix with each other,
wherein the injection member comprises:
the first hollow tube disposed in a center of the respective tube; and
a plurality of supports formed in radial shapes extending outward from the first hollow tube and in contact with the respective tube,
wherein a fuel injection hole configured to inject the fuel supplied from the fuel supply part in a direction opposite to a flow direction of the compressed air supplied from the air supply part and is formed in an upstream part of each of the supports,
wherein a central axis of the fuel injection hole is formed to be inclined at an angle with respect to a central axis of the respective tube so that the fuel is injected toward the center of the respective tube,
wherein the swirl vane comprises:
a second hollow tube communicating with the first hollow tube; and
a plurality of blades formed in spiral shapes on an outer circumferential surface of the second hollow tube,
wherein the central axis of the fuel injection hole extends from an exterior surface of the respective tube to an exterior surface of the upstream part of a respective support of the supports at the angle.

### Claim 2 (depends on 1)

The nozzle assembly of claim 1, wherein the fuel supply part comprises:
a fuel supply tube disposed in a center of the hollow nozzle frame and formed along a longitudinal direction of the hollow nozzle frame; and
a return member configured to move fuel supplied through the fuel supply tube to a rear side of the hollow nozzle frame.

### Claim 3 (depends on 2)

The nozzle assembly of claim 2, wherein the fuel injection hole configured to allow the return member and the inside of the respective tube to communicate with each other and is formed in the injection member so that the fuel supplied through the return member flows into the respective tube.

### Claim 4 (depends on 1)

The nozzle assembly of claim 1, wherein the supports comprise five supports and are disposed at equal angles from each other.

### Claim 5 (depends on 1)

The nozzle assembly of claim 1, wherein a fuel supply hole configured to allow the fuel supply part and the respective tube to communicate with each other and to supply the fuel of the fuel supply part to the respective tube is formed in the respective tube.

### Claim 6 (depends on 5)

The nozzle assembly of claim 5, wherein a central axis of the fuel supply hole is formed to be inclined with respect to the central axis of the respective tube so that the fuel is injected toward the center of the respective tube.

### Claim 7

A combustor configured to mix compressed air supplied from a compressor of a gas turbine with fuel and to combust a mixture of the compressed air and the fuel, the combustor being configured to supply a generated combustion gas to a turbine of the gas turbine, and the combustor comprising:
a nozzle casing;
a liner connected to an end portion of the nozzle casing adjacent to the turbine, the liner having an inner portion provided with a combustion chamber in which the mixture of the compressed air and the fuel is combusted;
a transition piece connected to an end portion of the liner adjacent to the turbine, the transition piece being configured to supply the generated combustion gas generated from the combustion chamber to the turbine; and
a nozzle assembly mounted inside the nozzle casing and configured to inject the fuel and the compressed air into the combustion chamber, wherein the nozzle assembly comprises:
a hollow nozzle frame;
a mixture supply tube having a plurality of tubes configured to supply the mixture of the compressed air and the fuel to the combustion chamber;
a fuel supply part configured to supply fuel to the mixture supply tube;
an air supply part configured to supply the compressed air to the mixture supply tube; and
a mixing part comprising:
an injection member formed in each of the plurality of tubes and configured to inject the fuel supplied from the fuel supply part into a respective tube of the plurality of tubes and toward the compressed air passing through the respective tube, with the injection member comprising a first hollow tube having a central flow path, through which the fuel and the compressed air flows, formed therein; and
a swirl vane formed on one side of the injection member, with the swirl vane having a flow path formed in a center thereof such that the flow path communicates with the central flow path of the first hollow tube and having blades formed on an outer surface thereof so that the fuel and the compressed air supplied from an outside of the first hollow tube mix with each other,
wherein the injection member comprises:
the first hollow tube disposed in a center of the respective tube; and
a plurality of supports formed in radial shapes extending outward from the first hollow tube and in contact with the respective tube,
wherein a fuel injection hole configured to inject the fuel supplied from the fuel supply part in a direction opposite to a flow direction of the compressed air supplied from the air supply part and is formed in an upstream part of each of the supports,
wherein a central axis of the fuel injection hole is formed to be inclined at an angle with respect to a central axis of the respective tube so that the fuel is injected toward the center of the respective tube,
wherein the swirl vane comprises:
a second hollow tube communicating with the first hollow tube; and
a plurality of blades formed in spiral shapes on an outer circumferential surface of the second hollow tube,
wherein the central axis of the fuel injection hole extends from an exterior surface of the respective tube to an exterior surface of the upstream part of a respective support of the supports at the angle.

### Claim 8 (depends on 7)

The combustor of claim 7, wherein a fuel supply hole configured to allow the fuel supply part and the respective tube to communicate with each other and to supply the fuel of the fuel supply part to the respective tube is formed in the respective tube, and a central axis of the fuel supply hole is formed to be inclined with respect to the central axis of the respective tube so that the fuel is injected toward the center of the respective tube.

### Claim 9

A gas turbine comprising:
a compressor configured to compress air introduced from outside;
a combustor configured to mix compressed air supplied from the compressor with fuel and to combust a mixture of the compressed air and the fuel; and
a turbine configured to generate power for generating electric power by passing a generated combustion gas supplied from the combustor through an inner portion of the turbine,
wherein the combustor comprises:
a nozzle casing;
a liner connected to an end portion of the nozzle casing adjacent to the turbine, the liner having an inner portion provided with a combustion chamber in which the mixture of the compressed air and the fuel is combusted;
a transition piece connected to an end portion of the liner adjacent to the turbine, the transition piece being configured to supply the generated combustion gas supplied from the combustion chamber to the turbine; and
a nozzle assembly mounted inside the nozzle casing and configured to inject the fuel and the compressed air into the combustion chamber,
wherein the nozzle assembly comprises:
a hollow nozzle frame;
a mixture supply tube having a plurality of tubes configured to supply the mixture of the compressed air and the fuel to the combustion chamber;
a fuel supply part configured to supply the fuel to the mixture supply tube;
an air supply part configured to supply the compressed air to the mixture supply tube; and
a mixing part comprising:
an injection member formed in each of the plurality of tubes and configured to inject the fuel supplied from the fuel supply part into a respective tube of the plurality of tubes and toward the compressed air passing through the respective tube, with the injection member comprising a first hollow tube having a central flow path, through which the fuel and the compressed air flows, formed therein; and
a swirl vane formed on one side of the injection member, with the swirl vane having a flow path formed in a center thereof such that the flow path communicates with the central flow path of the first hollow tube and having blades formed on an outer surface thereof so that the fuel and the compressed air supplied from an outside of the first hollow tube mix with each other,
wherein the injection member comprises:
the first hollow tube disposed in a center of the respective tube; and
a plurality of supports formed in radial shapes extending outward from the first hollow tube and in contact with the respective tube,
wherein a fuel injection hole configured to inject the fuel supplied from the fuel supply part in a direction opposite to a flow direction of the compressed air supplied from the air supply part and is formed in an upstream part of each of the supports,
wherein a central axis of the fuel injection hole is formed to be inclined at an angle with respect to a central axis of the respective tube so that the fuel is injected toward the center of the respective tube,
wherein the swirl vane comprises:
a second hollow tube communicating with the first hollow tube; and
a plurality of blades formed in spiral shapes on an outer circumferential surface of the second hollow tube,
wherein the central axis of the fuel injection hole extends from an exterior surface of the respective tube to an exterior surface of the upstream part of a respective support of the supports at the angle.

### Claim 10 (depends on 9)

The gas turbine of claim 9, wherein a fuel supply hole configured to allow the fuel supply part and the respective tube to communicate with each other and to supply the fuel of the fuel supply part to the respective tube is formed in the respective tube, and the central axis of the fuel supply hole is formed to be inclined with respect to a central axis of the respective tube so that the fuel is injected toward the center of the respective tube.