Gas turbine and bleeding method thereof

1. 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.

2. A gas turbine according to claim 1 , comprising a swirling flow generating device which converts bleed air for supplying the second and subsequent stage units into swirling flow rotating in a same direction of rotation of the units in the second bleeding line.

3. A gas turbine according to claim 2 , comprising a bleeding pipe for leading bleed air from the compressor into a rotor disk of a final stage unit of the susequent stage units in the second bleeding line, wherein the swirling flow generating device is a TOBI nozzle which is connected to a discharge port of the bleeding pipe,

and wherein the bleed air which is led to the final stage unit flows towards the second stage unit in a direction opposite to a direction in which the combusted gas flows.

4. A gas turbine according to claim 2 , comprising a bleeding flow path for leading bleed air from the compressor into stationary blades of units other than the first stage unit, wherein the swirling flow generating device is a TOBI nozzle which is provided in each inside shroud of the stationary blades introducing the bleed air from the bleeding flow path.

5. A bleeding method of a gas turbine comprising the steps of:

annularly providing plural stationary blades at an interior side of a vehicle;

annularly providing plural moving blades around plural rotor disks adjacent to stationary blades;

providing plural stage units comprising the stationary and moving blades;

introducing bleed air into each stage unit from a compressor;

supplying bleed air extracted from a final stage of the compressor into a first stage unit; and

supplying bleed air extracted from compressed air which has not yet arrived at a final stage unit of the compressor, said bleed air being provided 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 subsequent stage units.

6. A bleeding method of a gas turbine comprising a step of converting bleed air for supplying the second and subsequent stage units into swirling flow which rotates in a same direction of rotation of the units, wherein said bleed air is provided 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 first moving blades on a first subsequent stage unit of the susequent 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 second moving blades on a second susequent stage unit of the susequent stage units.