an integrated outlet guide vane assembly for turbomachinery typically includes at least one outlet guide vane and at least one bifurcation having a leading edge and a trailing edge . the turbomachinery has a central axis of rotation and a defined direction of rotation about the axis . the guide vane comprises an airfoil having a leading edge and a trailing edge and has a non - zero angle of lean in the direction of rotation and a non - zero sweep angle relative to a line perpendicular to the central axis . the leading edge of the bifurcation has a non - zero angle of lean in the direction of rotation and a non - zero sweep angle relative to a line perpendicular to the central axis . the trailing edge of the vane is faired into the leading edge of the bifurcation .