DOUBLE-FLOW TURBOJET ENGINE WITH FLOW MIXING, AXIRADIAL COMPRESSOR, HIGH-PRESSURE COMPRESSOR OF AXIRADIAL TYPE

摘要

FIELD: mechanical engineering. SUBSTANCE: proposed double-flow turbojet engine with flow mixing contains compressor, annular straight-flow combustion chamber and compressor turbine. Compressor includes propeller, axiradial highpressure compressor and axial-flow low-pressure compressor. Propeller has smaller number of blades rigidly secured inside front ring carrying disk. Axiradial single-stage high-pressure compressor is arranged in first circuit, and blades of its rotor are installed on two carrying disks parallel to axis of rotation of rotor. Low-pressure axial-flow compressor consists of one or several stages and is arranged in second circuit, its first stage being rigidly secured inside rear ring-shaped disk. Combustion chamber has no flame tubes, it is arranged before compressor turbine and provides mixing of hot gases of first circuit with cold air of second circuit. EFFECT: provision of stable operation within all ranges, prevention of surges, reduced front dimensions of engine. 4 cl, 3 dwg