Patent ID: 6773225
Filing Date: 2004-08-10
Classification: F01D

Abstract:
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; and a 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.