Separated micro turbojet engine

The invention discloses a separated micro turbojet engine which comprises an axial flow compressor, a combustion chamber unit body, a stator casing, a generator, a bearing, a rotating shaft and a double-sided rotor, the rotating shaft penetrates through the axial flow compressor, the stator casing is arranged in the axial flow compressor, the generator and the bearing are arranged in the stator casing, and the double-sided rotor is arranged on the rotating shaft in a sleeving mode; the axial flow compressor pressurizes the air flow, and all parts in the stator casing can be cooled through flowing of the air flow, so that the difficulty of cooling work of the bearing and the generator is reduced. The input airflow pressure ratio in the combustion chamber unit body is increased, and the combustion efficiency is greatly improved; air flow generated by combustion blows the double-face rotor, the double-face rotor rotates to continuously pressurize the air flow, and the working requirement for ...