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

FIELD: machine building.

SUBSTANCE: gas-turbine engine turbine comprises outer, inner and intermediate casings, stage with nozzle diaphragm and rotor wheel with annular insertion above the rotor wheel, cooling system for the turbine and casing, and radial clearance adjuster. The said adjuster comprises annular insertions, outer, inner and intermediate casings. The intermediate casing is of conical form with radial flange. The annular insertion above the rotor wheel is fixed on the intermediate and inner casings. The turbine and casing cooling system consists of a valve, main pipeline connected to the upper cavity of the nozzle diaphragm, inner pipeline connected to the swirler, a front baffle with holes and holes in the disk.

EFFECT: effective control of radial clearances in turbine, increasing engine thrust in takeoff and afterburner mode, increasing turbine efficiency factor and reliability.

3 cl, 3 dwg