FIELD: machine building.
SUBSTANCE: gas-turbine engine comprises a compressor and a turbine and a unit to adjust radial clearances of at least one stage of the compressor and/or 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 radial clearance adjuster is made as an annular perforated insert from "shape memory" material in the compressor and/or turbine casing. The adjuster with clearance formation is set above the relevant rotor blades of at least one stage. The main line with flow regulator supplies cooling air to the clearance cavity. The engine casings are fitted by sensors to measure radial clearance which are connected by electric links with on-board computer.
EFFECT: it is provided for engine operating without stand-by heat or significant decrease of heating time due to effective adjustment of radial clearances.
4 cl, 11 dwg
