GAS TURBINE SPLIT RING

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 through 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), and 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 pattern (10), deformation is absorbed by the slits (6), and thus the thermal deformation can be suppressed.