Provided is a vane tip clearance management structure for a gas turbine which allows a vane tip clearance to be confirmed easily at the time of completing assembly. For this purpose, there are provided: a casing (3) rotatably supporting a rotor (2); stator vane retainer rings (11, 12, and 13) and a turbine vane ring (16) provided to have predetermined clearances from tips of rotor vanes (10 and 15) fitted in multiple steps to the rotor (2) inside in the radial direction of the casing (3); guide frames (26) penetrating the casing (3), the stator vane retainer rings (11, 12, and 13) and the turbine vane ring (16) in the radial direction and being supported by stepped portions (21a, 22a, 23a, and 24a); and rods (25) movably supported by the guide frames (26) and abutting on the tips of the rotor vanes (10 and 15). Clearances (C1 and C2) are measured based on the amounts of movement of the rods (25) relative to the guide frames (26).