HYBRIDISATION OF TURBOJET ENGINE COMPRESSORS Russian patent published in 2019 - IPC F02K3/06 F01D15/10 F02C3/113 F02C7/268 

FIELD: machine building.

SUBSTANCE: double-case double-flow turbojet engine comprises fan (S) located at gas generator inlet and limiting primary flow and secondary flow. Primary flow passes through said gas generator and comprises low pressure (1) compressor, high pressure compressor (2), combustion chamber (3), high pressure turbine (4) and low pressure turbine (5). Low-pressure turbine is connected to low pressure compressor via low-pressure rotary shaft (10). High-pressure turbine is connected to high pressure compressor via high-pressure rotating shaft (20). Turbojet engine also comprises electric power supply motor, which generates mechanical power supply device (8) to at least one of rotary shafts, power take-off device for power take-off, at least, from one of the rotating shafts, the parameters of which are calculated so as to select excess power relative to the need for actuation of the auxiliary devices of the turbojet engine and to convert said excess power into electric energy, and electric energy accumulation facility located between power take-off device and electric motor. Power is extracted at low-pressure rotating shaft and power is supplied to high-pressure rotating shaft.

EFFECT: invention is aimed at optimization of surge margin of compressors and improvement of operation of turbojet engine in mode of low gas during flight.

9 cl, 7 dwg