GAS TURBINE ENGINE Russian patent published in 2017 - IPC F02C3/20 F02C3/34 F01D5/16 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine comprises a housing, sealing the entrance to the housing cover electrolyte supply system arranged in the form of jets with a cavitator electrolyte entering the flow of intake air into the engine, the cell-cavitator necking channel with the central body. Moreover, the supply of a constant electric current from the battery to the elements of the cavitator is performed, for example, to his local narrowing, and to its central body. Combustion chamber outlet is provided with gas flow separator including supersonic nozzle, outer and inner coaxial tubes and channel to return subsonic flow back, into the combustion chamber. In this case, the guide vanes of the compressor of a gas turbine engine made damping cavity.

EFFECT: increase dynamic stability reserve gas turbine compressor, reducing the resistance of the guide vanes, enhancing the efficiency of the gas turbine engine.

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