BLADE-DISK ASSEMBLY FOR A GAS TURBINE AND GAS TURBINE

A blade-disk assembly (200) for a gas turbine (100) includes a blade (230) having a root part (235), a disk (210) having a disk slot (213), into which the root part (235) is inserted, and a fixing block (250) inserted into a block assembly groove (237) of the blade (230) and a block insertion groove (215) of the disk in a circumferential direction (D2) to retain an axial position of the blade (230) with respect to the disk (210).The gas turbine (100) includes a compressor (110) configured to draw in and compress external air, a combustor (104) configured to mix fuel with the external air compressed in the compressor (110) and to combust a mixture of fuel and the compressed air, and a turbine (120), which comprises the blade-disk assembly (200), in which the blade (230) and the disk (210) are assembled and rotated by a combustion gas discharged from the combustor (104).