Patent ID: 10633982

Abstract:
A gas turbine includes a housing; a rotor rotatably provided in the housing; a turbine blade to receive rotating force from combustion gas and rotate the rotor; a turbine vane to guide a flow of the combustion gas toward the turbine blade, the turbine vane having a turbine vane cooling passage for delivering cooling fluid to an inner wall of the turbine vane; and an impingement plate installed in the turbine vane cooling passage, the impingement plate having a plurality of injection holes through which the cooling fluid is injected onto the inner wall of the turbine vane, the injection holes formed at predetermined locations of the impingement plate, wherein the injection holes are formed differently depending on locations of the injection holes. A temperature gradient or thermal stress may be prevented from occurring in the turbine vane that is cooled by cooling fluid ejected from the impingement plate.