A gas turbine includes a blade ring which faces blades from the outer side in a radial direction perpendicular to a turbine shaft, and a channel provided in the blade ring 1 and through which a cooling medium is flowed. The channel includes an inner channel formed in the blade ring 1 , and a tubular outer channel which is connected to the inner channel, is disposed in an outer portion of the blade ring 1 , and extends in a circumferential direction of the blade ring 1 . The outer channel includes a plurality of fixing portions fixed to the blade ring 1 and a thermal stress absorbing portion disposed between the fixing portions adjacent in the circumferential direction and expandable and contractible in the circumferential direction.
1. A gas turbine comprising:
a blade ring which faces blades from the outer side in a radial direction perpendicular to a turbine shaft; and
a channel provided in the blade ring and through which a cooling medium is flowed, wherein
the channel includes:
an inner channel formed in the blade ring; and
a tubular outer channel which is connected to the inner channel, is disposed in an outer portion of the blade ring, and extends in a circumferential direction of the blade ring, and wherein
the outer channel includes:
a plurality of fixing portions fixed to the blade ring;
a thermal stress absorbing portion disposed between the fixing portions adjacent in the circumferential direction and is expandable in the circumferential direction;
a first outer channel configures a supply system; and
a second outer channel configures a discharge system, which is disposed so as to be adjacent to the first outer channel in a direction of the turbine shaft.
2. The gas turbine according to claim 1 , wherein the thermal stress absorbing portion is a bellows tube.
3. The gas turbine according to claim 1 , wherein the thermal stress absorbing portion is a tube bent so as to be folded in a direction crossing the circumferential direction.