GAS-TURBINE ENGINE Russian patent published in 2009 - IPC F02C7/12 

FIELD: engines and pumps.

SUBSTANCE: gas-turbine engine comprises external circuit and internal circuit, which has combustion chamber, compressor, cooled turbine with at least two stages, nozzle block installed between them, and interdisk cavity. Balancing cavity is formed by the last stage of compressor, the first stage of turbine, combustion chamber and engine shaft, and is separated from compressor flow path by labyrinth seal. Gas-turbine engine also comprises supply air duct, which communicates by its outlet via nozzle track cooling circuit to interdisk cavity of turbine and is installed in heat exchanger cooled circuit. Inlet of supply air duct communicates to air circuit of one of compressor stages. Balancing cavity of compressor is connected by air duct to outlet of air-gas line of cooled turbine.

EFFECT: higher reliability and prolongation of gas-turbine plant resource.

3 cl, 2 dwg