Turbine engine fan
View Patent ↗A turbine engine air blower including a rotor disk that includes, on an outer periphery thereof, longitudinal ribs, each including a radial lug for attaching the disk onto a downstream compressor rotor. The flanks of the lugs form abutments for holding vanes that are mounted onto the disk. A mechanism protecting flanks of the lugs is circumferentially inserted between the lugs and the vanes.
1. A turbine engine fan comprising:
a rotor disc including on its external periphery slots for mounting blade roots delimited by longitudinal ribs each including a radial lug for fixing the disc on a compressor rotor downstream, flanks of the lugs forming stops for holding the blades mounted on the disc; and
U-shaped clips mounted on the lugs, each U-shaped clip comprises two lateral tabs covering the flanks of the lugs,
wherein each U-shaped clip comprises a transverse wall applied to a radial upstream face of a lug and comprising an orifice aligned with a corresponding orifice in the lug for passage of a screw or bolt for fixing on the compressor rotor downstream, and
wherein the transverse wall of each U-shaped clip comprises at least one radial tab, an end of which extends towards an upstream side along a rib of the disc.
2. A fan according to claim 1 , wherein the U-shaped clips are engaged axially from an upstream side on the lugs.
3. A fan according to claim 1 , wherein each lateral tab comprises a longitudinal fold fitting on a stop of a flank of the lug.
4. A fan according to claim 3 , wherein each U-shaped clip comprises two radial tabs parallel and spaced apart circumferentially from each other.
5. A clip to protect flanks of a radial lug of a peripheral rib of a fan disc according to claim 4 , comprising:
two substantially parallel lateral tabs connected by a transverse wall,
wherein the transverse wall comprises a central orifice, and
wherein the transverse wall is extended by two angled tabs, free ends of which extend in a direction opposite to the lateral tabs of the clip.