A propeller for an aircraft turbomachine, said propeller having; - a hub (50) extending around a first axis comprising openings (50a) distributed around the first axis, each of said openings (50a) having a substantially radial orientation relative to the first axis and extending through the hub, - a system (34) for controlling the angular setting of a blade (10) which is mounted in each of the openings (50a), and - bearings (46, 48) for guiding the control system (34), which are mounted in each of the openings (50a), said guide bearings (46, 48) comprising two guide bearings (46, 48), one of which comprises two annular rows of angular contact coaxial balls (70, 72) having different diameters (D2, D3).
HELICE POUR UNE TURBOMACHINE D'AERONEF
PROPELLER FOR AN AIRCRAFT TURBOMACHINE
PROPELLER FÜR EINE FLUGZEUGTURBOMASCHINE
2024-07-24
Patent
Electronic Resource
French