| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To reduce a bias in a stress distribution which is generated in a radial direction-passage formed in a radial direction of a disk. <P>SOLUTION: A gas turbine 1 includes: a disk 114 rotating about a rotational axis RL by jointing turbine rotor blades whose lateral circumferential portions receive combustion gas generated from combustion of fuel and transmitting energy of the combustion gas received by the turbine rotor blades; and a radial direction-passage 13 which is a through-hole formed on the disk 114 from a side nearer to the rotational axis RL toward outside of the disk 114, by including a portion in which a length in a circumferential direction of the disk 114 is larger than a length in a direction parallel to the rotational axis RL, in a cross section on a virtual curved surface VO3 which is a curved surface having a rotational axis RL as the axial center, with every point on the curved surface equidistant from the rotational axis RL. <P>COPYRIGHT: (C)2009,JPO&INPIT</p> |
