| 摘要 |
A gas turbine 1 includes a disk 114 rotatable about a rotational axis RL, when turbine rotor blades for receiving combustion gas obtained by burning fuel are connected to the side periphery, and energy of the combustion gas received by the turbine rotor blades is transmitted, and a radial passage 13 that, in a cross-section at a virtual curved plane V03 that is a curved plane about the rotational axis RL and in which distances from all points on the curved plane to the rotational axis RL are all equal, is a hole formed to include a portion having a shape in which the length in the circumferential direction of the disk 114 is longer than the length in the direction parallel to the rotational axis RL, and is formed in the disk 114 from the side of the rotational axis RL toward the outside of the disk 114. |
