Cooling structure of stationary blade, and gas turbine

A cooling structure of a stationary blade comprising an inner shroud and an outer shroud at an inside and an outside of a blade, in which the outer shroud, the blade, and the inner shroud are cooled by cooling air to be sent to the outer shroud side,

• wherein a cavity is formed at an inner surface of the inner shroud into which cooling air passing through the blade is sent, and
• the inner shroud comprises:
• a collision plate having plural small holes which is provided at an interval from a bottom surface of the inner shroud to form a chamber between the bottom surface and the collision plate, for guiding the cooling air in the cavity from the small holes into the chamber;
• a leading edge flow path provided at a leading edge side along a width direction for guiding the cooling air in the chamber;
• a side flow path provided along both sides for guiding the cooling air in the leading edge flow path to a trailing edge side;
• a header formed along the width direction near the trailing edge for feeding the cooling air from the side flow path;
• and plural trailing edge flow paths formed at intervals along the width direction at the trailing edge side each having one end connected to the header and the other end being open at the trailing edge, for ejecting the cooling air in the header from the trailing edge.