REFRIGERANT RECOVERY TYPE GAS TURBINE

摘要

To improve reliability in operation of a gas turbine by suppressing thermal stresses applied onto a rotor of the gas turbine and thermal displacement thereof. In the gas turbine, a plurality of disks (12a) having a plurality of moving blades (7a), which are driven by combustion gas, annularly arranged on an outer periphery thereof, and spacers (11a) disposed between the disks (12a) are successively arranged in an axial direction to form a rotor (1a) shaft. A gap is formed between that area of the disk (12a) on a side of an axis of the rotor, which faces the spacer (11a), and the adjacent spacer (11a), and contact surfaces (16a) contacting both that area of the disk (12a) on a side of an outer periphery of the rotor, which faces the spacer (11a), and the adjacent spacer (11a) are formed. Further, third flow passages (10a) are provided on the disks (12a) for conducting a fluid to the gap.