涡扇发动机用于民用超音速飞机，包括：多级风扇（3），其特征在于，所述多级风扇每个阶段的风扇转子（31，33）带有转子叶片和一个Fanstator（32，34A，34B），其具有定子叶片; 经过多级风扇（3）的第一级风扇转子（31）的输入流道（4）; 主流动通道（6），其穿过涡轮风扇发动机的核心发动机; 和通过核心发动机的第二流动通道（5）。 在这种情况下，输入电流通道（4）被分成一次流通道（6）和二次流通道（5）。 据设想，在入口流动通道中的风扇（3）的所有阶段的风扇转子（31，33）被布置之前其分割成主流动通道（6）和次级流动通道（5）（4）。

Turbofan engine for a civilian supersonic aircraft, comprising: a multi-stage fan (3), wherein each stage of the multistage fans a fan rotor (31, 33) with rotor blades and a Fanstator (32, 34a, 34b) having stator blades; an input current path (4) leading through the fan rotor (31) of the first stage of the multistage fans (3); a primary flow channel (6) which passes through a core engine of turbofan engine; and a secondary flow channel (5) leading to the core engine over. 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 the stages of the fan (3) in the inlet flow channel (4) prior to its division into the primary flow channel (6) and the secondary flow channel (5) are arranged.