LASH OF THE TURBOJET MOTOR FAN, TURBOJET ENGINE FAN AND TURBOJET ENGINE Russian patent published in 2017 - IPC F01D5/14 

FIELD: engines and pumps.

SUBSTANCE: fan blade of turbojet engine contains shank, end part, front and back edges. The front edge of the blade has angle sweep, greater than or equal +28° on the section of the blade, which is located on the radial height, lying in the range from 60% to 90% of the total radial vane height, measured from its shank towards its end part. The front edge of the sweep angle is the difference, less than 10° between the minimum angle measured at the sweep of radial height minimum angle of sweep on the section of the blade, lying in the range from 20% to 90% of radial blades, height and sweep angle measured at the radial height, which is 10% more than the mentioned radial height minimum angle of sweep. Other inventions of the group belong to the fan of the turbojet engine and turbojet engine, including many of the above-mentioned blades.

EFFECT: group of inventions helps to improve aerodynamic, acoustic and mechanical characteristics of the fan blades of the turbojet engine.

5 cl, 4 dwg