Patent ID: 8079803

Claim:
A cooling air supply structure that is provided in a gas turbine in which compressed air compressed by a compressor is ignited by supplying fuel thereto in a combustion chamber and combustion gas thus generated is transferred to a turbine casing of the turbine, thereby generating rotating power of a rotor, and that supplies cooling air to a turbine rotor blade of the turbine, the cooling air supply structure comprising: an introducing passage that is provided within a turbine stationary blade fixed within the turbine casing, and connects an interior and an exterior of the turbine casing; a rotor cavity that is provided in the rotor, and forms a space having an opening along a circumferential direction of the rotor; a nozzle that is provided on an inner circumference of the turbine stationary blade in a manner that the nozzle communicates with the introducing passage, and that has an outlet for cooling air facing the opening of the rotor cavity, and a swirler at the outlet; a seal member provided between the turbine stationary blade and the rotor; a cooling passage provided within a fixing member that is fixed to the rotor and rotates therewith, and that fixes the turbine rotor blade; and a pressurizing passage that communicates the cooling passage to the rotor cavity, wherein the outlet of the nozzle and a connecting opening of the pressurizing passage on the rotor cavity are arranged so that distances of the outlet and of the connecting opening from a central axis line of the rotor in a radial direction of the rotor are same.