Patent ID: 8662844

Claim:
A turbine vane comprising: an outer shroud; an airfoil part that has a pressure surface curved in a concave shape and a suction surface curved in a convex shape; and an inner shroud that is connected to the outer shroud via the airfoil part, wherein the airfoil part comprises: cooling chambers that are spaces into which the inside of the airfoil part is partitioned, from a leading edge side to a trailing edge side of the airfoil part, by a partition wall, and that extend in a vane-longitudinal-section direction; insert cylinders each of which is disposed in each of the cooling chambers and each of which has a plurality of impingement holes on the pressure surface side and the suction surface side of the insert cylinder; film holes that are provided in the pressure surface side and the suction surface side of the vane body; and a pair of division parts provided on a leading edge side and a trailing edge side of an inner surface of each of the cooling chambers, for dividing a cavity space, which is formed between the inner surface of each cooling chamber and an outer surface of each insert cylinder, into a pressure-surface-side cavity space close to the pressure surface and a suction-surface-side cavity space close to the suction surface, wherein each of the insert cylinders comprises a partitioning part that extends from the leading edge side to the trailing edge side and that extends in the vane-longitudinal-section direction, wherein the inside of each of the insert cylinders is partitioned into a pressure-surface-side insert space close to the pressure surface and a suction-surface-side insert space close to the suction surface, and wherein the partitioning part extends directly between the pair of division parts.