Intermediate case for an aircraft turbomachine made from a single casting with a lubricant duct

An intermediate case for a twin spool turbomachine for an aircraft, comprising a hub, an outer shell and outlet guide vanes removably mounted at their ends on the hub and on the outer shell, and each of at least some of said outlet guide vanes performing a heat exchanger function and comprising a lubricant passage designed to be cooled by a fan flow following an outer surface of the outlet guide vane,

• wherein the intermediate case also comprises at least one lubricant duct passing along a circumferential direction of the hub and at least part of which is made from a single casting with said hub,
• wherein each outlet guide vane comprises holes through which attachment elements pass to fix said outlet guide vane to the hub,
• wherein said lubricant duct has at least three lateral openings spaced relative to one another along the circumferential direction, and respectively communicating with said lubricant passage of at least three of the outlet guide vanes, and
• wherein each lubricant duct extends in an annular configuration around an angular sector of approximately 360°.