| 摘要 |
PROBLEM TO BE SOLVED: To restrain a local temperature rise of divided pieces of gas turbine segment. SOLUTION: The gas turbine segment 10 is disposed at a position opposite to a tip of a moving blade 8 in an inner periphery of a gas turbine casing 1. The gas turbine segment is constituted by divided pieces 11 annularly arranged in a circumferential direction along an inner peripheral face of the turbine casing, and the divided pieces are spaced from each other at predetermined intervals of spaces 13 in the circumferential direction. In end faces 11a, 11b in the circumferential direction of each divided piece 11, the end face 11a upstream from a moving blade rotating direction R is connected to a divided piece inner peripheral face 11c with a gentle inclined face 11f. Since a whirling flow of combustion gas FR accompanied by rotations of the moving blade flows along the inclined face 11f when the moving blade passes through the space 13, the whirling flow of combustion gas FR does not collide with the end face 11a. Therefore, increase in heat transfer coefficient at the end face 11 caused by the collision is prevented to restrain the local temperature rise. |
