Turbine vane and gas turbine
An airfoil part includes a plurality of 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, by a partition wall, that extend in a vane-longitudinal-section direction, and that include division parts on inner walls of a body; insert cylinders that are disposed in the cooling chambers and that have a plurality of impingement holes; and film holes that are provided in the body. The insert cylinders include partitioning parts that extend from the leading edge side to the trailing edge side and that extend in the vane-longitudinal-section direction. The insides of the insert cylinders are partitioned into pressure-surface-side insert spaces close to a pressure surface and suction-surface-side insert spaces close to a suction surface.
1. 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.
2. A turbine vane according to claim 1 , wherein the partitioning parts have communication holes that connect the pressure-surface-side insert spaces to the suction-surface-side insert spaces.
3. A turbine vane according to claim 1 , wherein each of the suction-surface-side insert spaces is surrounded by the respective insert cylinder, the respective partitioning part, and pressure adjusting plates disposed on the outer shroud and the inner shroud.
4. A gas turbine comprising a turbine section having a turbine vane supported by a turbine casing, wherein
the turbine vane comprises: an outer shroud that is supported by the turbine casing; 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.
5. A turbine vane according to claim 1 , wherein the insert cylinders have a plurality of pressure-surface-side impingement holes that are connected to a pressure-surface-side insert space, and a plurality of suction-surface-side impingement holes that are connected to a suction-surface-side insert space.