Turbine vane, and turbine and gas turbine including the same

A turbine comprising:

• a rotor disk configured to be rotatable;
• and
• a plurality of turbine blades and turbine vanes which are installed on the rotor disk,
• wherein the turbine vane comprises an airfoil including a leading edge and a trailing edge, an inner shroud disposed at one end of the airfoil to support the airfoil, an outer shroud disposed at the other end of the airfoil to support the airfoil and configured to face the inner shroud, a first cooling passage and a second cooling passage configured to extend in a height direction thereof, a first passage bending part configured to connect the first cooling passage and the second cooling passage and to include a first curved surface curved in an arc shape around a first point which is positioned inside the inner shroud or the outer shroud, and a first partition wall configured to split the first cooling passage and the second cooling passage and extend in a height direction of the airfoil, a longitudinal end of the first partition wall being positioned further outward than an end of the airfoil,
• wherein the first passage bending part is positioned in a space formed inside the inner shroud or the outer shroud, and
• wherein the first partition wall comprises a plurality of porous plates which protrude from the first partition wall.

A gas turbine comprising:

• a compressor configured to compress air drawn thereinto from an outside;
• a combustor configured to mix fuel with air compressed by the compressor and combust a mixture of the fuel and the compressed air;
• and
• a turbine comprising a plurality of turbine blades configured to be rotated by combustion gas discharged from the combustor,
• wherein the turbine comprises a rotor disk configured to be rotatable, and a plurality of turbine blades and turbine vanes which are installed on the rotor disk,
• wherein the turbine vane comprises an airfoil including a leading edge and a trailing edge, an inner shroud disposed at one end of the airfoil to support the airfoil, an outer shroud disposed at the other end of the airfoil to support the airfoil and configured to face the inner shroud, a first cooling passage and a second cooling passage configured to extend in a height direction thereof, a first passage bending part configured to connect the first cooling passage and the second cooling passage, and a first partition wall configured to split the first cooling passage and the second cooling passage and extend in a height direction of the airfoil, a longitudinal end of the first partition wall being positioned further outward than an end of the airfoil,
• wherein the first passage bending part is positioned inside the inner shroud or the outer shroud, and
• wherein the first partition wall comprises a plurality of porous plates which protrude from the first partition wall, the plurality of porous plates being positioned on the first passage bending part.