The invention provides a single rotor minitype
turbofan engine adopting an axial flow oblique flow serial composite compressing
system. The structure of the single rotor minitype
turbofan engine adopting the axial flow oblique flow serial composite compressing
system is that
airflow of an outer duct of a
turbofan engine and the
airflow which enters into a
combustor of an inner duct are both supplied by the axial flow oblique flow serial composite compressing
system, the axial flow oblique flow serial composite compressing system adopts a combination of both an axial flow fan rotor and an oblique flow compressor rotor, and provides pressure boosting
airflow for both the inner duct and the outer duct. The serial axial flow fan rotor is relative to the portion of the inner duct, and directly forms an oblique flow compressor
impeller to a serial blade lattice form; a row of
stator impellers is arranged on the axial flow fan rotor corresponding to the portion of the outer duct, the air flow is adjusted to the rear direction of the
meridian plane through rectification deceleration, and flows into a turbofan engine outer duct bypass along the outer surface of an intermediary
cartridge receiver. The single rotor minitype turbofan engine adopting the axial flow oblique flow serial composite compressing system has the advantages of being capable of realizing to provide the pressure boosting airflow for the inner duct and the outer duct by the needs of the turbofan engine, lowering an
oil consumption rate of the engine, improving windward side thrust of each unit of the engine, and effectively improving voyage and enhancing load when the single rotor minitype turbofan engine adopting the axial flow oblique flow serial composite compressing system is applied in carriers of unmanned planes, loitering munitions, and the like.