Abstract: A nozzle for a combustor in which a fuel containing hydrogen is burned is provided. The nozzle includes a first tube disposed in a center of the nozzle and having a first diameter, a plurality of second tubes circumferentially disposed around the first tube to be spaced apart from the first tube and each having a second diameter smaller than that of the first tube, and a plurality of third tubes disposed around the first tube and each having a diameter smaller than the second diameter, wherein the first tube, the plurality of second tubes, and the plurality of third tubes are arranged in parallel with each other.

Abstract: A nozzle for a combustor in which a fuel containing hydrogen is burned is provided. The nozzle includes a first tube disposed in a center of the nozzle and having a first diameter, a plurality of second tubes circumferentially disposed around the first tube to be spaced apart from the first tube and each having a second diameter smaller than that of the first tube, and a plurality of third tubes disposed around the first tube and each having a diameter smaller than the second diameter, wherein the first tube, the plurality of second tubes, and the plurality of third tubes are arranged in parallel with each other.

Abstract: A nozzle, a combustor, and a gas turbine are capable of efficiently atomizing fuel. The nozzle includes an outer tube; a first inner tube installed in the outer tube and configured to form an air passage between the first inner tube and the outer tube; a second inner tube installed in the first inner tube and configured to form a main fuel passage between the first inner tube and the second inner tube and to form a pilot fuel passage within the second inner tube; and a splash plate configured to form a first space between the outer tube and the splash plate, the first space communicating with the main fuel passage and with the air passage, and to form an injection slot communicating with the first space, the splash plate having a front end and a diameter increasing toward the front end.

Abstract: A combustor includes a plurality of fuel nozzles arranged in a nozzle casing. Each fuel nozzle includes a first fuel injection passage disposed at the axial center of the fuel nozzle and configured to inject liquid fuel into a combustion chamber. A second fuel injection passage encloses the first fuel injection passage and injects liquid fuel into the combustion chamber at a predetermined spray angle with respect to a center line of the fuel nozzle. A first air injection passage encloses the second fuel injection passage and injects air to be mixed with the injected liquid fuel from the second fuel injection passage. At the combustion chamber end, opposing surfaces of the first and second fuel injection passages are each inclined with respect to the center line and are separated by a space through which the liquid fuel of the second fuel injection passage is injected.

Abstract: A nozzle, a combustor, and a gas turbine are capable of efficiently atomizing fuel. The nozzle includes an outer tube; a first inner tube installed in the outer tube and configured to form an air passage between the first inner tube and the outer tube; a second inner tube installed in the first inner tube and configured to form a main fuel passage between the first inner tube and the second inner tube and to form a pilot fuel passage within the second inner tube; and a splash plate configured to form a first space between the outer tube and the splash plate, the first space communicating with the main fuel passage and with the air passage, and to form an injection slot communicating with the first space, the splash plate having a front end and a diameter increasing toward the front end.

Abstract: A combustor includes a plurality of fuel nozzles arranged in a nozzle casing. Each fuel nozzle includes a first fuel injection passage disposed at the axial center of the fuel nozzle and configured to inject liquid fuel into a combustion chamber. A second fuel injection passage encloses the first fuel injection passage and injects liquid fuel into the combustion chamber at a predetermined spray angle with respect to a center line of the fuel nozzle. A first air injection passage encloses the second fuel injection passage and injects air to be mixed with the injected liquid fuel from the second fuel injection passage. At the combustion chamber end, opposing surfaces of the first and second fuel injection passages are each inclined with respect to the center line and are separated by a space through which the liquid fuel of the second fuel injection passage is injected.