To provide a gas turbine which can be operated at high efficiency by securely and smoothly cooling an inner circumferential side surface of a shroud of the gas turbine.
A gas turbine provided with a shroud 41s forming a passage on the outer circumferential side of a bucket of the gas turbine is provided with a cavity 41c to which cooling medium is introduced, an intake port to take cooling medium introduced from an axial direction position of the cavity 41c on the downstream side of a first bucket 41b into the cavity 41c is taken, and a convection cooling passage 41d provided with an exit 41e at an axial direction position of the shroud 41s on the upstream side of the first bucket 41b and formed along an inner circumferential surface of the shroud 41s in which cooling medium taken from the intake port flows.
KITSUKA NOBUAKI
ANZAI SHUNICHI
KAWAIKE KAZUHIKO
