Abstract: A turbomachine subassembly has a radially inner shell and a radially outer shell of an annular gas flow path. A radial arm extends radially between the radially inner and outer shells and delimits an isolated volume which is connected to an inner volume of a chamber partly delimited by the radially inner shell. A segment of a conduit extends radially in the isolated volume, and a ventilation air supply source is connected to supply ventilation air to the isolated volume, whereby ventilation air may be supplied to the chamber through the isolated volume. An external radial end of the radial arm supports a first connection box that closes it off. The internal volume of the radial arm communicates with the ventilation air supply source. An external cylindrical wall of the first connection box fits inside an internal cylindrical wall of the external radial end of the radial arm.

Abstract: A turbomachine subassembly including an annular gas flow path is delimited by a radially inner shell and a radially outer shell, a radial arm between the inner shell and the outer shell, that delimits an isolated volume of the annular flow path, which is connected to the inner volume in which a segment of a conduit, and ventilation air supply to a chamber delimited at least partly by the inner shell, through one radial arm, wherein the volume delimited by the radial arm is connected to the inner volume of the chamber and to a ventilation air supply source, wherein the external radial end of the arm supports a first connection box that closes off the external radial end of the arm, that includes a device for connecting the segment to the remainder of the conduit and a device for connecting the internal volume of the arm to the ventilation air supply source.

Abstract: A turbomachine for an aircraft, comprising a rotor shaft, a turbomachine case, a lubricated bearing chamber, at least one bearing supporting the rotor shaft and being located in the bearing chamber, a lubrication device comprising oil injection means to inject oil into the bearing chamber, and oil supply means to supply oil to said oil injection means, and an electric current generator, comprising an armature driven by the rotor shaft and a field coil fixed to the turbomachine case. The generator has an orifice, which passes longitudinally through the generator from one end to the other, and the oil injection means pass through the orifice so that oil can circulate in the axial direction through the generator.