FIELD: engines and pumps.
SUBSTANCE: unit of a fan on a blade comprises radially internal and radially external aerodynamic surfaces, passing, accordingly, radially inside and radially outside from a circular shroud, and internal and external chords. Internal and external chords pass between the internal and external front and rear edges of cross sections of internal and external aerodynamic surfaces, accordingly, of radially external and internal aerodynamic surfaces. The circular shroud is arranged along the circumference with a centre at the axial line. Internal and external angles of inclination between the internal and external chords, accordingly, on the shroud and the axial line, differ from each other. The turbofan gas turbine engine comprises the described fan unit on the blade.
EFFECT: increased efficiency of operation at high ratios of pressure at the fan hub and pressure of the air jet of external contour, to ensure high specific draft in the mode of takeoff and climb, and also during operation at low pressure ratios of the air jet of the second contour.
12 cl, 9 dwg
