| 摘要 |
PROBLEM TO BE SOLVED: To reduce axial thrust, improve the cooling efficiency of blades and disks and contrive uniform temperature distribution in axial-flow gas turbines by disposing a suction device for removing leakage air and a portion of cooling air in the area of a drum labyrinth. SOLUTION: A main portion of cooling air to a rotor 3 is led into a wheel- side chamber 19 via lines 22 and swirl nozzles 23. A major portion of the swirling cooling air is introduced into a cooling duct 24 in the rotor 3, while a minor portion thereof is introduced into a gas duct in a turbine 1 defined between a turbine disk and a disk cover. Another swirl nozzle 23 spaced less radially from the principal turbine axis than the above swirl nozzles 23 guides separate cooling air toward the wheel-side chamber 19. The separate cooling air flows along an annular duct 20 from the opposite end of a compressor 10 until it is sucked, along with a leakage air mass flow trapped after a rearmost moving blade 11, by suction devices 25 disposed in the area of a drum labyrinth 21.
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