Cooling device for a gas turbine fixed shroud

摘要

The device has two axial sections (48, 54) for passage of air. The sections channel the air that comes from an impact cavity (36) and that tends to leak via upstream fastener systems into upstream circumferential space (52). The sections direct the air towards an upstream recess (18) of ring segments (10) before being evacuated into hot gas passage (6) in order to cool upstream shoulder (22) of the ring segments. An independent claim is also included for a fixed ring surrounding a hot gas passage of a gas turbine comprising a cooling device.