Patent ID: 6783323
Filing Date: 2004-08-31
Classification: B23K,F01D,F05D

Abstract:
A gas turbine stationary blade comprising:a stationary blade section provided therein with a passage configured to pass cooling air; an inner shroud configured to support the stationary blade section on a side of a discharge port of the cooling air; and a plurality of segments including the stationary blade portion and the inner shroud, which are coupled to one another in an annular form, wherein at least one flow passage extends from the discharge port of the cooling air of the stationary blade section, and the flow passage extends to a corner section on a side of a front edge of the inner shroud and extends rearward along a side edge of the inner shroud, and wherein the flow passage is widened in a front edge corner section of the inner shroud, and a regulating plate is disposed on a floor of the widened flow passage.