Patent ID: 8313283

Claim:
A vane tip clearance management structure for a gas turbine, comprising: an outer casing rotatably supporting a rotor; an inner casing provided so as to have a predetermined clearance from tips of rotor vanes which are fitted in multiple steps to the rotor on the inner side of the casing in the radial direction, said inner casing having a hole opening in a radial direction, said hole including a stepped portion located on an outer peripheral surface side of said inner casing; a guide frame having a large diameter portion and a small diameter portion and a screw hole, which communicates with a through hole formed in the center of the guide frame, is formed in the large diameter portion and a flange portion formed on the small diameter portion, in which said small diameter portion of said guide frame penetrating the outer casing and the inner casing in the radial direction and a lower portion of said flange portion being supported by said stepped portion of the inner casing; and a rod, which is inserted in said through hole, is movably supported by the guide frame so as to allow said rod to be fixed by a setscrew provided in the screw hole when said rod abuts on the tip of the rotor vane, and wherein the predetermined clearance formed between said inner casing and said tips of said rotor vanes is based on a length of the guide frame, a length of the rod, a thickness of the inner casing, and the amount of movement of the rod relative to the guide frame.