Abstract: A nozzle, a combustor, and a gas turbine are capable of uniformly pre-mixing fuel and air. The nozzle includes an integrated swirler comprising an inner tube configured to provide a first pre-mixing passage through which pre-mixed air flows, an outer tube configured to partially enclose the inner tube and form an outer fuel passage through which fuel flows, and a plurality of vanes coupled with the outer tube, each vane having an exhaust hole through which fuel exits; a fuel injector including an inner fuel passage through which fuel flows and being configured to be inserted into the inner tube of the integrated swirler; and a peg having an outer surface in which are formed a plurality of injection holes communicating with the inner fuel passage, the injection holes configured to inject the fuel of the inner fuel passage into the first pre-mixing passage.

Abstract: A combustor has a structure enabling selective control of the amount of air supplied to the liner and the transition piece and includes a liner having one end connected to a fuel injector, the liner comprising an inner liner surrounded by an outer liner having a first opening that is elongated in a circumferential direction of the outer liner and is configured to introduce cooling air into an annular space between the inner liner and the outer liner; a liner sliding cover configured to adjust an opening degree of the first opening; and a transition piece connected at one end to the other end of the liner and connected to a turbine at the other end, the transition piece having an effusion hole configured to supply cooling air to a combustion chamber, the effusion hole having an opening area that is less than the opening degree of the first opening.

Abstract: A nozzle, a combustor, and a gas turbine are capable of uniformly pre-mixing fuel and air. The nozzle includes an integrated swirler comprising an inner tube configured to provide a first pre-mixing passage through which pre-mixed air flows, an outer tube configured to partially enclose the inner tube and form an outer fuel passage through which fuel flows, and a plurality of vanes coupled with the outer tube, each vane having an exhaust hole through which fuel exits; a fuel injector including an inner fuel passage through which fuel flows and being configured to be inserted into the inner tube of the integrated swirler; and a peg having an outer surface in which are formed a plurality of injection holes communicating with the inner fuel passage, the injection holes configured to inject the fuel of the inner fuel passage into the first pre-mixing passage.

Abstract: A combustor has a structure enabling selective control of the amount of air supplied to the liner and the transition piece and includes a liner having one end connected to a fuel injector, the liner comprising an inner liner surrounded by an outer liner having a first opening that is elongated in a circumferential direction of the outer liner and is configured to introduce cooling air into an annular space between the inner liner and the outer liner; a liner sliding cover configured to adjust an opening degree of the first opening; and a transition piece connected at one end to the other end of the liner and connected to a turbine at the other end, the transition piece having an effusion hole configured to supply cooling air to a combustion chamber, the effusion hole having an opening area that is less than the opening degree of the first opening.