Patent ID: 7017349

Claim:
A gas turbine comprising: plural stationary blades which are annularly provided at an interior side of a vehicle; plural moving blades which are annularly provided around plural rotor disks adjacent to stationary blades; plural stage units comprising the stationary and moving blades; a compressor for supplying bleed air into stage units; a first bleeding line for supplying bleed air into a first stage unit; and a second bleeding line, other than the first bleeding line, for supplying bleed air into a second stage unit and subsequent stage units, wherein said second bleed line is connected to a plurality of cavities connected in series, wherein one cavity of the plurality of cavities has a first plurality of radially extending holes provided at angular distances from one another on a first rotor disk and configured to provide flow paths to moving blades on a first subsequent stage unit of the subsequent stage units, and wherein the one cavity has a second plurality of radially extending holes provided at angular distances from one another on a second rotor disk and configured to provide flow paths to moving blades on a second susequent stage unit of the susequent stage units.