GAS TURBINE ENGINE TURBINE Russian patent published in 2013 - IPC F01D11/24 F02C7/12 

FIELD: engines and pumps.

SUBSTANCE: radial clearance adjustment means is composed of ring inserts, inner, outer and mid casings. Said conical mid casing is equipped with radial flange. Ring insert above impeller is secured to mid and inner casings. Turbine cooling systems comprise common valve. Casing cooling system comprises manifold and holes in outer casing. Turbine cooling system comprises main pipeline connected with distributor upper cavity, inner pipeline connected with swirler, front deflector with holes and holes in disc. Ring insert inner surface may be provided with soft rubbing coating. Inner surface of every circular insert may be proved with cellular seal panels secured thereat.

EFFECT: efficient control over radial clearance, higher takeoff and augmenter thrust, efficiency and reliability.

3 cl, 7 dwg