Turbomachinery (10) for aircraft, including:-At least one first turbine rotor (22a) is connected to the first turbine shaft (36) and has rotor blades located in a vein (V),-An annular exhaust crankcase (28) supporting at least one guide bearing (60, 62) when the first shaft rotates, including an arm (28a) located in the vein downstream of the blade, and-A planetary planetary gear mechanical reducer (42) comprises a sun gear (44), a bevel gear (40) and a satellite carrier (46), The reducer is at least partially surrounded by the exhaust housing, and one of the rotating moving parts selected from the sun gear and the reducer crown connected with the first shaft,The utility model is characterized in that the exhaust crankcase is provided with a (70) device, which is used for recovering and discharging the ejected oil by centrifugal method during the operation of the reducer.Abstract figure: Figure 3
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