Gas turbine and bleeding method thereof
AssigneeMitsubishi Heavy Industries, Ltd.
InventorsVincent Laurello, Masanori Yuri
Life of this patent
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Abstract
Bleeding is operated by annularly providing plural stationary blades at an interior side of a vehicle; annularly providing plural moving blades around rotor disk 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.
Claims6
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.
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.
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.
Dependencies are inferred from the claim text.