SINGLE-SHAFT TURBOJET BYPASS FAN ENGINE Russian patent published in 2025 - IPC F02K3/06 F01D15/10 

FIELD: engine building.

SUBSTANCE: single-shaft turbojet bypass fan engine comprises a confuser of initial acceleration of air flow, fan with a profile of blades operating at supersonic speeds of air flow, a starter-generator based on a brushless DC electric machine built into the central part of the fan impeller, multistage axial compressor compressing air flow of internal circuit of engine, combustion chamber of annular type, turbine with profile of blades of active type, having one or several impellers. Fan, starter-generator, axial compressor and turbine are installed on one shaft without using reduction gears. Parameters of blades, fan, compressor and turbine are optimized so that reduction of impellers is not required. Technical solution can be used in engines with a bypass ratio of up to 8.

EFFECT: invention improves weight and size characteristics of bypass engines while maintaining good efficiency.

1 cl, 1 dwg