Recovery of lubricating oil from a reduction gear of an aircraft turbine engine

An aircraft turbine engine, said turbine engine having a longitudinal axis and comprising:

• at least one first turbine rotor connected to a first turbine shaft and comprising rotor vanes located in a duct,
• an annular exhaust casing supporting at least one bearing for guiding in rotation said first shaft about the axis and comprising arms located in said duct, downstream of said vanes, and
• a mechanical reduction gear with epicyclic gear train of the planetary type which comprises a sun gear, a ring gear, and a planet carrier, the reduction gear being at least partly surrounded by said exhaust casing and one of the elements that can rotate about the axis selected from the sun gear and the ring gear of the reduction gear being connected to said first shaft,
• wherein the exhaust casing carries a device for recovering and evacuating oil centrifugally sprayed in operation by the reduction gear, said device comprising an annular oil recovery gutter which extends around the reduction gear and which is connected to at least one oil evacuation conduit which passes through one of said arms of said exhaust casing.