GAS-TURBINE ENGINE Russian patent published in 2003 - IPC

FIELD: mechanical engineering. SUBSTANCE: proposed gas-turbine engine contains combustion chamber, compressor connected by shaft with cooled turbine, compressor dummy space located between last stage of compressor, first stage of turbine, combustion chamber and shaft connecting compressor with turbine and separated from compressor setting by labyrinth seal. Labyrinth seal contains at least one straight tooth and mating flange arranged, respectively, on rotor and stator of compressor and at least two backward teeth with mating flanges arranged on compressor stator by means of blind walls and forming intermediate air space. Turbine has at least two stages with nozzle assembly blades and interdisk space between stages. Blades of nozzle assembly are provided with partition dividing inner space into front and rear spaces. Outlet of supply air pipe connecting inner space of nozzle assembly blades with dummy space is located at inlet into front space of nozzle assembly blades. Outlet of front space communicates with inner air manifold formed by inner flanges of nozzle assembly blades and shell mounted on blades and communicating, in its turn, with gas-air duct of turbine. Rear space of nozzle assembly blades communicates with interdisk space of turbine. EFFECT: improved reliability of engine and increased service life at preservation of economy. 6 cl, 4 dwg