To provide a turbine moving blade capable of preventing occurrence of damage or stress concentration causing the damage by certainly keeping a connection force of an annular blade row and suppressing partial contact of a blade groove provided on the outer periphery of a rotor with a dovetail during turbine operation.
The turbine moving blade comprises the dovetails 2 pressed into the blade grooves 8 formed on the outer periphery of a disk 6 of the rotor 7, blade parts 3 extending from the dovetails 2, and integral shrouds 4 at the upper ends of these blade parts 3, and the integral shrouds 4 are interconnected to form the annular blade row. A circumferential end surface of each integral shroud 4 is provided with mutually overlapping projections 4a, 4b having a gradient in the axial direction.
| JP2009264378 | SHAPE FOR TURBINE BUCKET TIP SHROUD |
| WO/2010/046283 | BLADE FOR A GAS TURBINE |
SAITO EIJI
NAMURA KIYOSHI
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