To provide a rotor blade which can be favorably manufactured and provides same level of durable years as normal durable years of a forged blade root by modifying a rotor blade 13 for fixing a rotor 10 of a compressor of a gas turbine including a blade 14 and the blade root 15 extending along a blade axial line, retaining the rotor blade 13 between two intermediate members 12, 18 circumferentially continuing in an annular groove 11 by the blade root, engaging the blade root 15 with adjoining intermediate members 12, 18 from a lower side by a plurality of projections 16, 16' constructed in T-shape lateral section surface and extending in a circumference direction, and engaging the intermediate members with an undercut 24 of the groove 11 in a blade axial line direction by a retention surface 20.
The T-shape blade root 15 is cut by milling. Relief grooves 21, 30 extending in a direction of the blade axial line A1 are provided respectively in order to reduce mechanical stress at transition parts from the blade root to the projection parts 16, 16'.
| JP2595958 | [Name of device] Impeller |
| JP6159131 | Turbo machinery bucket attachment system |
Toshiomi Yamazaki
Takuya Kuno
Hiroshi Sugimoto
Kimihiro Hoshi
Hiroyasu Ninomiya
Einzel Felix-Reinhard
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