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In order to provide a gas turbine and a gas bleeding method which can prevent the loss of drive power due to gas bleeding to the rotor disk, bleed gas is imparted with swirling flow in the same rotational direction as that of a first stage rotor disk by being passed through a set of TOBI nozzles whi

In order to provide a gas turbine and a gas bleeding method which can prevent the loss of drive power due to gas bleeding to the rotor disk, bleed gas is imparted with swirling flow in the same rotational direction as that of a first stage rotor disk by being passed through a set of TOBI nozzles which constitute a flow conduit therefor, and is supplied to this first stage rotor disk, with a portion of this bleed gas flow being bypassed and being supplied between first stage stationary blades and first stage moving blades.

대표청구항 ▼

1. A gas turbine, comprising:a plurality of stationary blades arranged in a circular manner on a near side of a turbine casing;a plurality of moving blades arranged in a circular manner on a near side of a rotor disk adjoining said stationary blades;a swirling flow generating section configured to g

1. A gas turbine, comprising:a plurality of stationary blades arranged in a circular manner on a near side of a turbine casing;a plurality of moving blades arranged in a circular manner on a near side of a rotor disk adjoining said stationary blades;a swirling flow generating section configured to generate a swirling bleed gas flow by imparting a swirling flow to a portion of a bleed gas supplied thereto and to supply said swirling bleed gas flow to said rotor disk, wherein said swirling bleed gas flow rotates in the same rotational direction as that of said rotor disk; anda seal gas supply flow conduit configured to supply a remaining portion of said bleed gas to a gap between said stationary blades and said moving blades, bypassing said swirling flow generating section,wherein said seal gas supply flow conduit extends between swirling flow generating members in said swirling flow generating section. 2. A gas turbine, comprising:a plurality of stationary blades arranged in a circular manner on a near side of a turbine casing;a plurality of moving blades arranged in a circular manner on a near side of a rotor disk adjoining said stationary blades;a swirling flow generating section configured to generate a swirling bleed gas flow by imparting a swirling flow to a portion of a bleed gas supplied thereto and to supply said swirling bleed gas flow to said rotor disk, wherein said swirling bleed gas flow rotates in the same rotational direction as that of said rotor disk; anda seal gas supply flow conduit configured to supply a remaining portion of said bleed gas to a gap between said stationary blades and said moving blades, bypassing said swirling flow generating section,wherein said swirling flow generating section has outside, inside, upstream, and downstream regions and comprises a plurality of TOBI nozzles configured to reduce a flow conduit cross sectional area while swirling from the outside in a radial direction towards the inside around a rotational axis of said rotor disk as a center; andwherein a portion of said seal gas supply flow conduit is disposed so as to pass between said TOBI nozzles. 3. A method of bleeding gas for a gas turbine, which comprises a plurality of stationary blades arranged in a ring shape on a near side of a turbine casing, and a plurality of moving blades arranged in a ring shape on a side of a rotor disk adjoining said stationary blades, the method comprising:generating a swirling bleed gas flow by imparting a swirling flow to a portion of a bleed gas, wherein said swirling bleed gas flow rotates in the same rotational direction as that of said rotor disk;supplying said swirling bleed gas flow to said rotor disk; andsupplying a remaining portion of said bleed gas to a gap between said stationary blades and said moving blades,wherein said seal gas supply flow conduit extends between swirling flow generating members in said swirling flow generating section. 4. A method of bleeding gas for a gas turbine, which comprises a plurality of stationary blades arranged in a ring shape on a near side of a turbine casing, and a plurality of moving blades arranged in a ring shape on a side of a rotor disk adjoining said stationary blades, the method comprising:generating a swirling bleed gas flow by imparting a swirling flow to a portion of a bleed gas, wherein said swirling bleed gas flow rotates in the same rotational direction as that of said rotor disk;supplying said swirling bleed gas flow to said rotor disk; andsupplying a remaining portion of said bleed gas to a gap between said stationary blades and said moving blades, wherein:said generating a swirling bleed gas flow further comprises a swirling flow generating section having outside, inside, upstream, and downstream regions and a plurality of TOBI nozzles configured to reduce a flow conduit cross sectional area while swirling from the outside in a radial direction towards the inside around a rotational axis of said rotor disk as a center, andsaid s upplying said remaining portion of said bleed gas further comprises supplying said remaining portion through a flow conduit disposed so as to pass between said TOBI nozzles.