| 摘要 |
<p>PROBLEM TO BE SOLVED: To provide a structure for a gas turbine blade, capable of greatly reducing a stress generated in a tip shroud and suppressing deformation of the tip shroud by effectively reinforcing high stress parts or deformable regions of the tip shroud provided in a blade end portion.SOLUTION: A gas turbine blade includes a tip end shroud 10 including: a cover 15 extending from a tip end of the gas turbine blade in a circumferential direction of the blade and in a direction of a rotary shaft of the blade; and a plurality of fins 16 extending from the cover 15 to an opposite side to the blade along a rotation radius direction of the blade. The gas turbine blade includes, on a surface of the cover 15 on which the fins 16 are provided, a cover-back-side circumferential end portion located close to a rear edge with respect to a back-side circumferential end portion of a rear edge fin 16b; a first reinforcement 21 passing through a back-side front edge of a blade-surface extension surface and coupling the cover-back-side circumferential end portion to a front edge fin 16a; a cover-body-side circumferential end portion located close to a front edge with respect to a body-side circumferential end portion of the front edge fin 16a; and a second reinforcement 22 passing through a body-side rear edge of the blade-surface extension surface and coupling the cover-body-side circumferential end portion to the rear edge fin 16b.</p> |
