| 摘要 |
A gas turbine split ring having an increased rigidity for suppressing a thermal deformation and the reduced number of splits for reducing the amount of leakage of cooling air from a connection part, wherein cooling air (70) from a compressor flows through cooling holes (61) in an impingement plate (60) into a cavity (62), strikes and cools the split ring (1), enters throug h openings (63) in the cavity (62) into a plurality of cooling passages (64), flows through the passages (64) to cool the inside of the split ring (1), an d is discharged from a peripheral side surface (64) to a gas passage, whereby, because a waffle pattern (10) is formed on the bottom surface of the split ring (1) and a plurality of slits (6) are provided in the flanges (4) and (5 ) in circumferential direction, the rigidity is increased by the waffle patter n (10), deformation is absorbed by the slits (6), and thus the thermal deformation can be suppressed.
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