Propeller for an aircraft turbomachine

A propeller for an aircraft turbomachine, this propeller comprising:

• a hub extending around a first axis and comprising openings distributed around this first axis, each of these openings having a radial orientation with respect to said first axis and passing through said hub,
• a control system for controlling an angular pitch of a vane which is mounted in each of said openings, and
• guide bearings for guiding the control system, which are mounted in each of said openings,
• said control system comprising:
• a vane comprising a blade connected to a root, the vane comprising a pitch axis which is radial with respect to said first axis,
• a bowl extending around said pitch axis, the bowl comprising an inner housing for receiving the root of the vane, and
• elements for attaching and securing the root of the vane against rotation with respect to the bowl,
• said guide bearings comprising:
• a first ball bearing extending around said pitch axis and said root, between a radially external end of said bowl and said hub, and
• a second ball bearing which extends around said pitch axis and said root, between a radially internal end of said bowl and said hub,
• wherein said second ball bearing comprises two annular rows of balls which are coaxial and with angular contact, a first of these rows having a first diameter and a second of these rows having a second diameter smaller than the first diameter, at least one plane perpendicular to said pitch axis passing through the first and second rows of balls.