GAS TURBINE

Blade ring cooling passages (14, 15) are provided inside a first blade ring (8) and a second blade ring (9). The blade ring cooling passages (14, 15) are connected with each other through a communication pipe (16) that is arranged in an axial direction of the blade ring. From outside of a wheel chamber (1), cooling air (17) to cool down stationary blades is sent with pressure into inside of the stationary blades which are installed inner wall of the blade rings. Thermal shields (18) are provided on outer surfaces of the blade rings (8, 9) and communication pipes (16) through gaps therebetween. In the gaps between the outer surfaces of the blade rings (8, 9) or the outer surfaces of the communication pipes (16) and the thermal shields (18), partitions are installed to stagnate the cooling air (17) to cool down the stationary blades.