PROBLEM TO BE SOLVED: To reduce stress acting a rotor and to improve operation reliability of a gas turbine by providing flow passage flowing axially on an axial direction overlapping part of plural disks in a rotor where a supplying passage for axially moving refrigerant of a moving blade into a disk and a spacer is provided. SOLUTION: During operation of a gas turbine, while mainstream gas flows from a first-stage moving blade 5 toward a fourth-stage moving blade 8, refrigerant is supplied from the central hole 15 of a stub shaft 13, and flows through a cavity 16, and the central hole 17 of a fourth-stage hollow disk 4 to the central hole 18 of a 3-4 spacer 11. Then, the refrigerant travels through a slit 20 formed on a joining surface 19 between the 3-4 spacer 11 and a third-stage hollow disk 3 to supplying holes 21, 22. Then, the refrigerant flows through a supplying hole 23 penetrating through a secondstage hollow disk 2 and a slit 25 formed on a joining surface 24 between a 2-3 spacer 10 and a second- stage hollow disk 2 to a cavity 26, and is supplied through radial direction hole 27 on the outer periphery side of the second-stage hollow disk 2 to a second-stage moving blade 6.