SUPERSONIC AIRCRAFT JET ENGINE Russian patent published in 2012 - IPC B64C30/00 B64D33/00 F02C7/00 

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to jet engine air intake. Air intake comprises air intake scarf and cowling edge. Said scarf and edge are configured to make first oblique shock wave (CS) extending outward from scarf front to stay ahead of edge, and closing shock wave extending outward from scarf rear to area ahead of edge or directly to edge. Scarf comprises first section relative to minor concavity configured to make the system of initial shock wave extending from first section ahead of edge and within the airflow path via air intake. Second intermediate straight section of scarf is configured to create flow with constant Mach number. Third section is located behind said second section relative to minor concavity configured to create the system of extra oblique shock wave. Said extra oblique shock wave extends from third section so that system crosses said closing shock wave within incoming air entrapped between scarf and edge systems. Fourth straight section of scarf is configured to create airflow with constant Mach number coupled with air flowing through medium section of air intake. Fifth section ensures initial turning of flow toward engine ahead of closing shock wave. Air intake system serves to create shock wave compression system and full pressure distribution system, full pressure being knowingly irregular over whatever axial plane located behind closing shock wave.

EFFECT: efficient operation at low take-off speed to high-speed cruise.

15 cl, 18 dwg