Outlet guide vane for aircraft turbine engine, presenting an improved lubricant cooling function

A guide vane to be arranged in all or part of an air flow of an aircraft turbine engine fan with dual flow, the guide vane comprising:

• a foot;
• a head;
• and
• an aerodynamic part for straightening the air flow arranged between the foot and the head of the guide vane, said aerodynamic part of the guide vane comprising a first inner duct for lubricant cooling extending according to a first main direction of lubricant flow from the foot to the head of the guide vane, said first inner duct being partly bounded by a pressure side wall and a suction side wall of the guide vane,
• wherein the aerodynamic part of the guide vane is embodied as one piece including heat transfer fins, arranged in the first duct connecting the pressure side and suction side walls and expanding substantially parallel to the first direction, and
• wherein the heat transfer fins are spaced from each other according to the first direction and in a transverse direction of the guide vane from a leading edge towards a trailing edge of the aerodynamic part, so that at least some of the heat transfer fins are significantly arranged staggered.