TURBOFAN ENGINE Russian patent published in 2025 - IPC F02K3/06 F02K3/11 

FIELD: mechanical engineering.

SUBSTANCE: invention relates to aircraft engineering. Turbofan engine comprises: compressor drive module (1), fan drive module (2), compressor drive module (1), consisting of input device (3), low pressure compressor (4), high pressure compressor (5), main combustion chamber (6), high pressure turbine (7), low pressure turbine (8), exhaust device (9), made in such a way that in the main combustion chamber the heat supplied to the working medium is converted into the compressor drive mechanical work, and there is no gas flow kinetic energy increment, fan drive module (2), consisting of additional combustion chamber (10), turbine (11) installed on one shaft with fan (14) located in nacelle (15), nozzle (13), said module is arranged so that heat fed to working fluid in extra combustion chamber is, mainly, converted into fan drive mechanical work while another portion is used to increase kinetic energy of gas flow in the nozzle.

EFFECT: increasing the reliability and service life of the turbofan engine.

1 cl, 2 dwg