GAS-TURBINE ENGINE BLADE STRUT INSERT AND ROTOR DISK UNIT Russian patent published in 2006 - IPC F01D5/32 

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: proposed rotor disk unit of gas-turbine engine contains row of ring hubs, great number of dovetail slots spaced over circumference, great number of fan blades and great number of blade strut inserts. Each hub encloses central line, being connected with disk rim by bridge. Dovetail slots arranged in rim pass in circumference between disk posts. Posts of disk pass in axial direction from front end to rear end of rim, ad in radial direction, inwards from outer surface of disk rim. Fan blades have roots in form of dovetail fitted in dovetail slots. Each strut insert is arranged inside each of dovetail slots between bottom wall of dovetail slot and lower surface of dovetail root passing in axial direction. Strut insert contains base passing in axial direction, front, middle and rear dovetail fastening flats arranged at a distance form each other, space passing around base and between front and rear dovetail fastening flats of root, and strut insert lip. Fastening flats are arranged along base. Lip of strut insert receded mainly in axial direction forwards from front flat and it is provided with intersecting holes passing in axial and radial directions. Base and front, middle and rear dovetail fastening flats are provided with curved lower surfaces. Each front, middle, and rear dovetail fastening flat is provided with rose over base and flat upper surface.

EFFECT: increased draught of fan without increasing size of blades, provision of reliable fastening of blades.

19 cl, 29 dwg