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

The invention relates to a turbomachine front part (1) of a dual-stream aircraft comprising a single blower (15), a gas generator (2) arranged downstream of the blower (15), a gearbox (20) interposed between the gas generator (2) and the blower (15), a flow separation spout (21) and a structure (44) with a structural outlet guide vanes (42). According to the invention, the blades (42) each have a foot arranged upstream of the flow separation nozzle (21), and said reducer (21) is also arranged at least half upstream of said flow separation nozzle (21). ).