Impingement cooled ring segment of a gas turbine

摘要

A gas turbine in which the cooling efficiency of the ring segment is improved. The gas turbine comprises static vanes (3) disposed between adjacent movable vanes (2) and adapted to be operated by a main combustion gas (15) flow through a casing, said casing including a plurality of the ring segements (90) disposed so as to surround the tip ends of said movable vanes (2), and a plurality of impingement cooling plates (92) arranged to surround an outside periphery of said ring segments (90) so as to define a ring segment cavity (96) therebetween. The ring segment cavity (96) is divided in the axial direction by a pressure partition plate (97) extending in the circumferential direction between said ring segments (90) and said impingement cooling plates (92) so as to provide plural cavities including an upstream cavity (96a) and a downstream cavity (96b). Each of said plural cavities (96a,96b) is open to the tip ends of said movable vanes (2) at a position different in the axial direction through a ring segment cooling path (93a,93b) passing through from an outside peripheral side of said ring segment (90) to an inside peripheral side thereof and extending in the downstream direction. <IMAGE>