GAS TURBINE

摘要

A gas turbine is provided with: a turbine rotor blade (33); a turbine stator blade (32); a dividing ring (52) surrounding the turbine rotor blade (33) in a circumferential direction; an outer shroud (51) surrounding the turbine stator blade (32) in the circumferential direction; and a combustion gas flow channel (R1) disposed in the dividing ring (52) and the outer shroud (51) for circulating combustion gas. The outer shroud (51, 51a) is positioned upstream of the dividing ring (52, 52a) in a gas flow direction of the combustion gas. A seal gas with a temperature lower than the combustion gas is supplied from between the dividing ring (52a) and the outer shroud (51a) toward the combustion gas flow channel (R1). The outer shroud (51a) includes a guide surface (61) disposed on an inner circumference of the outer shroud (51a) downstream in the gas flow direction for guiding the internally circulated combustion gas toward an inner circumferential surface of the dividing ring (52a). The guide surface (61) is formed such that the flow channel area of the combustion gas flow channel (R1) can be increased.