Fan for a turbomachine

A jet engine, comprising:

• a fan comprising at an intake, fan blades, an annular casing, a hub rotating around an axis of the turbomachine, said hub comprising a fan disc bearing the fan blades, which fan blades extend radially relative to said axis in an annular stream delimited internally by the hub and externally by the annular casing, wherein:
• said fan has an intake diameter (A), which corresponds to the diameter of the circle comprising the radially outer ends of the fan blades, of a value of between 900 mm and 1200 mm and has a hub ratio, which corresponds to a ratio of the diameter (B) of the inner limit of the stream at the radially inner ends of the leading edges of the fan blades, divided by the intake diameter, of a value of between 0.20 and 0.265, and
• the hub comprises a fan disc comprising at an outer circumference ribs formed in alternation with grooves in which blades roots of the fan blades are engaged, each groove having a groove bottom, and
• a shim having a radial thickness of between 1 mm and 3 mm is interposed radially between one of said blade roots and one of said groove bottoms, and
• a low-pressure compressor arranged downstream from the fan disc and which abuts directly against downstream ends of the blade roots and the ribs of the fan disc, wherein said fan disc has an outer limit, formed by outer ends of the ribs, a diameter of which is between 245 mm and 275 mm, and an inner limit formed by an inner end of an inner wall of the fan disc, a diameter of which is between 120 mm and 140 mm.