TURBOJET ENGINE FAN ROTOR Russian patent published in 2004 - IPC

FIELD: turbojet engines. SUBSTANCE: fan rotor of turbojet engine has great number of detachable blades 18 secured on rim 12 of disk 10. Each fan blade 18 has root part 16 fitted in groove, mainly axial in direction, and of corresponding shape and made in rim 12 of disk 10. Each blade 18 of fan is held in groove by means of key 20 found under each root 16 of blade, and devices designed for holding keys 20 and root parts 16 of blades 16 axially. Said devices contain, in particular, flange 24 thrusting against surface of disk 10 front in direction of flow and connected to disk 10 by means of corresponding fasteners. Keys 20 are provided with thickening 22 on one of ends between root parts 16 of blades and flange 24. disk is provided with great number of radial projections 26 on its surface front in direction of flow, said projections alternate with grooves. Flange 24 is provided with great number of radial teeth 28 on its surface rear in direction of flow, capable of getting into thrust contact with radial projections 26 of disk 10. flange fastening devices are located on its part inner in radial direction. EFFECT: provision of holding blades in cascade manner in case of axial displacement. 4 cl, 6 dwg