Nozzle assembly, combustor and gas turbine comprising the same

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.

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.