TURBINE STATIONARY BLADE COOLING STRUCTURE

PROBLEM TO BE SOLVED: To provide a turbine stationary blade cooling structure for effectively cooling an inside shroud at its trading side (at the rear part of a nozzle band portion) without discharge machining a finely elongate hole in a gas turbine having a high temperature at the inlet while applying itself as it is to position changes of a band flange portion of a turbine nozzle or a cooling jet orifice. SOLUTION: The turbine stationary blade cooling structure is located between a combustor and a turbine moving blade for introducing high temperature gas from the combustor to the turbine moving blade on the downstream side. A turbine stationary blade 10 consists of a plurality of nozzle segments 12 divided in the peripheral direction. Each nozzle segment has a hollow cavity 13a provided in the inside shroud, a cooling air passage 13b via which the hollow cavity is communicated with the cooling air supply face of the inside shroud, and a cooling air jet orifice 11 via which the hollow cavity is communicated with the high temperature gas flow face of the inside shroud. COPYRIGHT: (C)2005,JPO&NCIPI