A turbine cooling circuit (32) includes a flow sleeve (34) having an aft end (36) for adjoining the rim (30a) of a turbine disk (30). A seal rotor (38, 42) is spaced from the aft end adjacent a row of inlet holes (40). An inducer (46) has an outlet (50) di...

In a closed circuit moving blade cooled turbine, holes in the radial direction formed in the outer periphery of a second stage wheel are led to cooling air supply holes to second stage moving blades and to prevent the cooling air from leaking into the junc...

The invention relates to a cooling air guidance system in the high-pressure turbine section of a gas turbine engine, wherein a portion of the air flow exiting the compressor section of the engine and guided past the gas turbine combustor is conducted via a...

In a gas turbine having a structure of collecting a refrigerant after cooling the moving blades, a plurality of wheels having a plurality of moving blades including cooling paths in the outer periphery and a plurality of spacer members are alternately arra...