A gas turbine blade equipped with a blade cooling structure, comprising: a cooling passage which is formed in the interior of the blade and extends from a proximal end portion, where the blade is to be supported by a rotor, to a blade portion of the blade, the blade portion having a leading end, wherein the cooling passage has an inlet for communicating with a fluid passage formed within the rotor and supplying cooling air, and an outlet, the direction from the proximal end portion to the leading end of the blade portion defining the radial direction of the blade, wherein the cooling passage is formed by a dorsal wall portion, a ventral wall portion and a partition wall constituting the blade portion, wherein a height of the cooling passage is the distance between the wall surface of the dorsal wall portion and the wall surface of the ventral wall portion opposing each other, wherein a longitudinal direction of the cooling passage is the extending direction of the cooling passage in the radial direction of the blade which defines the main flow direction of cooling air through the cooling passage, and wherein a width of the cooling passage is the dimension perpendicular to the height of the cooling passage and perpendicular to the longitudinal direction of the cooling passage; a plurality of turbulators arranged in multiple stages with an equal pitch in the longitudinal direction of the cooling passage on both wall surfaces of the dorsal wall portion and the ventral wall portion of the cooling passage opposing each other, in such a manner so as to protrude from the respective wall surface by a predetermined amount of protrusion (e), so as to extend over the entire region of the width of the cooling channel, and so as to be inclined with respect to the longitudinal direction of the cooling passage; and the blade being characterized by the outlet opening at the leading end of the blade portion and by a plurality of dimples formed on the wall surface of the cooling passage only in a region which is downstream in the longitudinal direction of the cooling channel of a center position of the pitch between adjacent turbulators. a cooling passage which is formed in the interior of the blade and extends from a proximal end portion, where the blade is to be supported by a rotor, to a blade portion of the blade, the blade portion having a leading end, wherein the cooling passage has an inlet for communicating with a fluid passage formed within the rotor and supplying cooling air, and an outlet, the direction from the proximal end portion to the leading end of the blade portion defining the radial direction of the blade, wherein the cooling passage is formed by a dorsal wall portion, a ventral wall portion and a partition wall constituting the blade portion, wherein a height of the cooling passage is the distance between the wall surface of the dorsal wall portion and the wall surface of the ventral wall portion opposing each other, wherein a longitudinal direction of the cooling passage is the extending direction of the cooling passage in the radial direction of the blade which defines the main flow direction of cooling air through the cooling passage, and wherein a width of the cooling passage is the dimension perpendicular to the height of the cooling passage and perpendicular to the longitudinal direction of the cooling passage; wherein the cooling passage has an inlet for communicating with a fluid passage formed within the rotor and supplying cooling air, and an outlet, the direction from the proximal end portion to the leading end of the blade portion defining the radial direction of the blade, wherein the cooling passage is formed by a dorsal wall portion, a ventral wall portion and a partition wall constituting the blade portion, wherein a height of the cooling passage is the distance between the wall surface of the dorsal wall portion and the wall surface of the ventral wall portion opposing each other, wherein a longitudinal direction of the cooling passage is the extending direction of the cooling passage in the radial direction of the blade which defines the main flow direction of cooling air through the cooling passage, and wherein a width of the cooling passage is the dimension perpendicular to the height of the cooling passage and perpendicular to the longitudinal direction of the cooling passage; a plurality of turbulators arranged in multiple stages with an equal pitch in the longitudinal direction of the cooling passage on both wall surfaces of the dorsal wall portion and the ventral wall portion of the cooling passage opposing each other, in such a manner so as to protrude from the respective wall surface by a predetermined amount of protrusion (e), so as to extend over the entire region of the width of the cooling channel, and so as to be inclined with respect to the longitudinal direction of the cooling passage; and the blade being characterized by the outlet opening at the leading end of the blade portion and by a plurality of dimples formed on the wall surface of the cooling passage only in a region which is downstream in the longitudinal direction of the cooling channel of a center position of the pitch between adjacent turbulators.