Patent ID: 6966750

Claim:
A gas turbine stationary blade comprising: a stationary blade section provided therein with a passage for cooling air; an inner shroud for supporting the stationary blade section on the side of a discharge port of the cooling air; and a plurality of segments each of which includes at least one of the stationary blades and at least one of the inner shrouds, and which are coupled to one another in an annular form, wherein the segments are assembled in such a manner that a side end face of the inner shroud is connected to that of another inner shroud of an adjacent segment by using a bolt joint, wherein at least one flow passage is pulled out from the discharge port of the cooling air of the stationary blade section, and the flow passage is introduced to a corner section on the side of a front edge of the inner shroud and is extended rearward along a side edge of the inner shroud.