公开(公告)号：US10167731B2

公开(公告)日：2019-01-01

申请号：US14922647

申请日：2015-10-26

Applicant: Snecma

Inventor： Augustin Marc Michel Curlier ,  Nicolas Maurice Herve Aussedat ,  Gwénolé Yann Le Pache

IPC: F01D15/10 ,  H02K7/18 ,  F01D11/02 ,  F01D25/16 ,  F01D25/18 ,  F01D25/24 ,  F16N7/36 ,  H02K9/19

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.