(57) A gas turbine includes a rotor shaft comprising a plurality of discs (8, 9, 10, 11,
12a). Each disc (8, 9, 10, 11, 12a) has a plurality of moving blades (4, 5, 6, 7,
7a) driven by combustion gas and arranged annularly on the peripheral portion. Spacers
(11a, 13, 14, 15) are arranged between the discs (8, 9, 10, 11, 12a), the respective
discs (8, 9, 10, 11, 12a) and the spacers (11a, 13, 14, 15) being arranged in the
axial direction. The moving blades (4, 5, 6, 7, 7a) are provided with flow paths (8a,
9a) for introducing coolant for cooling and discharging the coolant heated by the
combustion gas. Contact surfaces (16a, 31, 32, 33, 34, 35, 36) contacting both the
discs (8, 9, 10, 11, 12a) in rotor peripheral side regions and adjacent spacers (11a,
13, 14, 15) are formed therebetween. A supply flow path (8a) passes through the discs
(8, 9, 10, 11, 12a) and the spacers (11a, 13, 14, 15) in the regions forming the contact
surfaces (16a, 31, 32, 33, 34, 35, 36) and supply the coolant for cooling the moving
blades (4, 5, 6, 7, 7a). A recovery flow path (9a) recovers the coolant which is heated
by the moving blades (4, 5, 6, 7, 7a).
|
|