Patent ID: 8317466

Claim:
A blade structure of a gas turbine comprising stationary blades that are arranged annularly in a casing and rotor blades that are arranged annularly on a rotor that is rotatable about an axis of rotation, the stationary blades and the rotor blades being alternately arranged to form a plurality of stages in a direction of the axis of rotation, and a gap being provided between outer edge portions of the rotor blades and the casing, wherein assuming that a height of each of the stationary blades in a radial direction of the rotor is 100%, each of the stationary blades located downstream of the rotor blade, between which and the casing the gap is provided, includes a border section at a position of 80% of the height of the stationary blade outward in the radial direction from an inner edge portion of the stationary blade, and at least a part of a section located outward of the border section in the radial direction is bent towards a rotational direction of the rotor so that a stagnation line, that is a boundary between a combustion gas flowing into a side of a back surface and a combustion gas flowing into a side of a ventral surface, in the section located radially outward of the border section is aligned in a circumferential direction around the axis of rotation with the stagnation line in a section located radially inward of the border section.