| 摘要 |
PROBLEM TO BE SOLVED: To improve inserting performance of an insert into a nozzle cavity inside of a gas turbine, and to improve the strength of the connection part of the insert with the nozzle. SOLUTION: The insert 70, having plural openings for collision-cooling a nozzle stationary blade of a nozzle segment inside of a gas turbine, is inserted into one end of a stationary blade. The tip of the insert is stopped at a position slightly away from a rib provided near the other end of the stationary blade, into which the insert is inserted. The insert forms or swages this end into a shape corresponding to the shape of the inner edge of the rib. The insert is brazed or welded to the rib. |
