Outlet guide vane for aircraft turbomachine, comprising a lubricant cooling passage equipped with flow disturbance studs

Guide vane that will be arranged in all or part of an air flow stream of a fan of a twin spool aircraft turbine engine, the guide vane comprising a root, a tip and an aerodynamic part straightening the flow stream arranged between the vane root and tip, the vane comprising an extrados body defining at least part of an extrados surface of the aerodynamic part, and an intrados body defining at least part of an intrados surface of the aerodynamic part, this comprising at least one internal lubricant cooling passage equipped with flow disturbing studs and delimited at least partly by the intrados and extrados body fixed to each other,

• wherein a first series of studs is made in a single piece with the extrados body, the studs of the first series defining a first inter-stud space between them,
• in that a second series of studs is made in a single piece with the intrados body, the studs of the second series defining a second inter-stud space between them through which studs of the first series pass while the studs of the second series pass through the first inter-stud space,
• and in that the end of the studs of the first series is located at a distance from the intrados body, and the end of the studs of the second series is located at a distance from the extrados body.