FRONT AIRCRAFT TURBOMACHINE PART COMPRISING A SINGLE BLOWER CONDUCTED BY A REDUCER, AS WELL AS STRUCTURAL OUTPUT LEAD DIRECTORS FITTED PARTLY BEFORE A SEPARATION SPOUT

摘要

A front part of an aircraft turbomachine of the bypass type including a single fan, a gas generator positioned downstream of the fan, a reducer interposed between the gas generator and the fan, a flow splitter and a structure with structural outlet guide vanes. The vanes each have a root arranged upstream of the flow splitter and the reducer is also arranged at least half upstream of the flow splitter.