Output director vane for an aircraft turbine engine, with an improved lubricant cooling function using a heat conduction matrix housed in an inner duct

摘要

A guide vane comprising an aerodynamic part (32, fig 2) comprising a first inner duct 50a extending in a first main direction 52a between a foot (34) and a head (36) of the vane. The duct is partly bounded by pressure and suction side walls 70, 72 of the vane and is suitable for holding lubricant which would flow in the first direction. Housed within the duct is a first heat conduction matrix, including rows of main heat transfer fins 80 which extend in the first direction. The rows are spaced from one another in the first direction and in a transverse direction (60) between the leading (64) and trailing edge (62) of the vane. Each row also includes junction fins which each connect two main fins directly in a consecutive manner in the transverse direction, where the junction fins are alternately in contact with the pressure side wall and the suction side wall. With their connecting main fins they form transverse structures in a cradle or u-shaped form. The heat conducting fins allow the external air or working fluid to cool the lubricant within the duct.