FIELD: aviation.
SUBSTANCE: aircraft contains a turbojet engine (10) with the opposite rotation fans. The turbojet engine (10) is integrated into the rear of the fuselage (2), continuing it, and contains two gas generators (12a, 12b) supplying the working turbine (14). The turbine (14) has two rotors of the opposite rotation (14a, 14b) configured to rotate the two fans (20a, 20b) located behind the gas generators (12a, 12b). For each gas generator (12a, 12b), separate air intakes (18a, 18b) are connected to the fuselage (2) so that, at least, part of the boundary layer formed around the fuselage (2) enters the air intakes.
EFFECT: invention reduces noise and fuel consumption.
6 cl, 2 dwg
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