GAS-TURBINE ENGINE Russian patent published in 2013 - IPC F01D11/20 

FIELD: machine building.

SUBSTANCE: gas turbine engine consists of a compressor and a turbine. The compressor comprises several axial stages including a casing, guide vanes and rotor blades. The turbine comprises a casing and at least one stage with a nozzle diaphragm and a rotor wheel. The engine comprises a unit to adjust radial clearances of at least one stage of the compressor and/or turbine. The radial clearance adjuster is made as an annular insert from semiconducting material in the compressor and/or turbine casing, it is set above the relevant rotor blades of at least one stage. The adjuster also consists of cores from magnetically conducting material with windings, the cores are fixed radially on the outer casing surface on both sides of the rotor blades of the relevant stage with even pitch.

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

4 cl, 10 dwg