A stator vane suitable for a gas turbine in which a plurality of stator vanes are disposed in an array in a circumferential direction (Dc) around a rotor shaft and in which a combustion gas flow passage is formed through which combustion gas (G) flows in operation, the stator vane comprising: a vane body that is to be disposed inside the combustion gas flow passage so as to extend in a radial direction (Dr) of the rotor shaft ; and a shroud (60i;60o) that is formed at an end of the vane body in the radial direction (Dr) and is to define a part of the combustion gas flow passage , wherein the shroud (60i;60o) has a gas path surface that faces the radial direction (Dr) and is to come in contact with the combustion gas (G), a pair of circumferential end surfaces that face opposite sides in the circumferential direction (Dc), a cavity into which cooling air can flow, and a plurality of circumferential blowout passages that communicate with the cavity and open in the circumferential end surface , the circumferential end surface has a central region that is a region located inside a throat circle (Sc) being a circle with a minimum radius of circles in contact with both the vane body of the stator vane and a vane body of another stator vane adjacent to the stator vane in the circumferential direction (Dc) in the mounted state, an upstream-side region that is located further on an upstream side (Dau) of the combustion gas flow passage than the central region , and a downstream-side region that is located on the opposite side (Dad) of the central region from the upstream side (Dau), and openings of the plurality of circumferential blowout passages are formed at least in the central region , characterized in that a density that is the number of the openings of the circumferential blowout passages per unit length in an axial direction (Da) in which the rotor shaft extends is higher in the central region than in the upstream-side region and the downstream-side region . a vane body that is to be disposed inside the combustion gas flow passage so as to extend in a radial direction (Dr) of the rotor shaft ; and a shroud (60i;60o) that is formed at an end of the vane body in the radial direction (Dr) and is to define a part of the combustion gas flow passage , wherein the shroud (60i;60o) has a gas path surface that faces the radial direction (Dr) and is to come in contact with the combustion gas (G), a pair of circumferential end surfaces that face opposite sides in the circumferential direction (Dc), a cavity into which cooling air can flow, and a plurality of circumferential blowout passages that communicate with the cavity and open in the circumferential end surface , the circumferential end surface has a central region that is a region located inside a throat circle (Sc) being a circle with a minimum radius of circles in contact with both the vane body of the stator vane and a vane body of another stator vane adjacent to the stator vane in the circumferential direction (Dc) in the mounted state, an upstream-side region that is located further on an upstream side (Dau) of the combustion gas flow passage than the central region , and a downstream-side region that is located on the opposite side (Dad) of the central region from the upstream side (Dau), and openings of the plurality of circumferential blowout passages are formed at least in the central region , characterized in that a density that is the number of the openings of the circumferential blowout passages per unit length in an axial direction (Da) in which the rotor shaft extends is higher in the central region than in the upstream-side region and the downstream-side region . <EOS>