PROPELLER FOR AN AIRCRAFT TURBINE ENGINE INCLUDING A BLADE-RETAINING RING MOUNTED AROUND A HUB

摘要

The invention relates to a propeller (1) for an aircraft turbine engine including a plurality of blades (2) as well as a hub (4) having a plurality of recess openings (5) receiving the blade roots, each root (8) being pivotably mounted in the corresponding recess opening (5) thereof. According to the invention, the propeller also has at least one structure (40) forming a ring for retaining the blades in the radial direction toward the outside relative to the hub (4), said structure being clamped around the latter.