Turbofan engine for a civil supersonic aircraft

摘要

The invention relates to a turbofan engine for a supersonic civil aircraft, comprising: a multi-stage fan (3), each stage of the multi-stage fan having a fan rotor (31, 33) with rotor blades and a fan stator (32, 34a, 34b) with stator blades ; an input flow channel (4) passing through the first-stage fan rotor (31) of the multi-stage fan (3); a primary flow channel (6) passing through a core engine of the turbofan engine; and a secondary flow passage (5) leading past the core engine. In this case, the input current channel (4) is divided into the primary flow channel (6) and the secondary flow channel (5). It is envisaged that the fan rotors (31, 33) of all stages of the fan (3) in the input stream channel (4) before the division into the primary flow channel (6) and the secondary flow channel (5) are arranged.