Electric power supply for apparatuses supported by the rotor of an aircraft engine

摘要

An aircraft engine including: a stator; a main shaft; a first rotor; a second rotor; a transmission mechanism; a first electrical apparatus supported by the first rotor and a second electrical apparatus supported by the second rotor; at least one first field winding supported by the stator; a control unit configured to circulate direct electric current in the first field winding; at least one first armature winding supported by the first rotor and connected to the first electrical apparatus and at least one second armature winding supported by the second rotor and connected to the second electrical apparatus.

主权项

1. An aircraft engine comprising:
a stator; a main shaft, a first rotor, and a second rotor; a transmission mechanism configured to convert rotation of the main shaft into rotation of the first rotor in a first direction and into rotation of the second rotor in a second direction opposite the first direction; at least one first electrical device carried by the s rotor and at least one second electrical device carried by the second rotor; at least one first field winding carried by the stator; a control unit configured to cause direct electric current to flow in first field winding; and at least one first armature winding carried by the first rotor and connected to the first electrical device and at least one second armature winding carried by the second rotor and connected to the second electrical device; the first field winding being disposed between the first armature winding and the second armature winding.