AERONAUTICAL PROPULSION SYSTEM HAVING A LOW LEAKAGE FLOW RATE AND IMPROVED PROPULSION EFFICIENCY

摘要

The present invention relates to an aeronautical propulsion system (1) comprising a reduction mechanism (12) that couples a drive shaft (10) and a fan shaft (13) comprising two reduction stages (27, 32) and including: - a sun gear (33), - an annulus (25), and - a series of planets (28) distributed circumferentially between the sun gear (33) and the annulus (25), each planet (28) comprising a first portion (38) meshing with the sun gear (33), and a second portion (39) meshing with the annulus (25), a diameter of the first portion (38) being different from a diameter of the second portion (39), the first portion (38) of the planets (28) extending between the second portion (39) of the planets (28) and the fan (2).