AIRBOARD TURBOMACHINE EXIT OUTPUT AUDE COMPRISING A LUBRICANT-BENDED ZONE HAVING AN IMPROVED DESIGN

摘要

The invention relates to a guide vane (24) for a turbofan aircraft turbomachine, its aerodynamic portion (34) comprising a first internal passage (50a) lubricant cooling in which are arranged thermal transfer means and a second lubricant cooling inner passage (50b) in which thermal transfer means is arranged, the aerodynamic portion comprising a welded zone (54) connecting a lubricant outlet end of the first inner passage (50a) to an inlet end lubricant of the second passage (50b), the bend zone extending along a curved generatrix and being partially defined by the intrados wall and the extrados wall of the blade. According to the invention, the bent zone (54) comprises one or more lubricant guides (84) arranged between the intrados and extrados walls of the blade, and each extending substantially parallel to the curve generatrix of the bent area (54).