Patent ID: 11913385
Assignee: SAFRAN TRANSMISSION SYSTEMS
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. An aeronautical propulsion system comprising:
a drive shaft rotationally movable about an axis of rotation,
a fan,
a fan shaft configured to rotationally drive the fan about the axis of rotation,
a reduction mechanism coupling the drive shaft and the fan shaft,
a compression section rotationally driven by the drive shaft,
an inlet channel that extends between the fan and the compression section, the inlet channel comprising an inner ferrule and an outer ferrule together delimiting an air inlet flow path in the compression section, the inner ferrule having a predetermined minimum radius,
wherein the reduction mechanism comprises two reduction stages including at least two planet gears circumferentially distributed around the axis of rotation, each planet gear comprising a first portion meshed with the drive shaft and a second portion meshed with the fan shaft,
wherein each planet gear is mounted fixed with respect to the inner ferrule of the inlet channel, and wherein
each planet gear has a predetermined maximum radius,
the predetermined maximum radius being greater than the predetermined minimum radius of the inner ferrule of the inlet channel such that the air inlet flow path extends at least partly between the at least two planet gears.