| 摘要 |
PROBLEM TO BE SOLVED: To provide a gas turbine that can restrain separation of flows of cooling air in blade bottom passages and reduce pressure losses.SOLUTION: The gas turbine comprises: a disk part 11a in which blade grooves are formed on an outer peripheral surface; rotor blades 10 including blade roots 10a fitted to the blade grooves; blade bottom passages 11e formed in the blade grooves along the axial direction of the disk part 11a by fitting the blade roots 10a to the blade grooves; and grooves 1A formed on an axial end surface of the disk part 11a, extending from the radial inside to the radial outside of the disk part 11a, and communicating with the blade bottom passages 11e. |
