Patent ID: 11881754
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Electrical machinery, apparatus, energy (Electrical engineering)
Classification: CPC H  F  Y | IPC F  H

Claim 5:
6. The turbomachine according to claim 5, comprising:
a gas generator having a longitudinal axis,
a fan located at an upstream end of the gas generator and configured to rotate about said axis, and
an electric machine with a generally annular shape which is mounted coaxially downstream of the fan, and which comprises a rotor rotatably coupled to the fan, and a stator connected by said bar to a power electronic circuit,
the fan being configured to generate a main gas flow, a portion of which flows into a primary annular duct of the gas generator to form a primary flow, and another portion of which flows around the gas generator to form a secondary flow,
the primary duct being delimited by a first and a second annular envelopes coaxial with the gas generator, the primary duct being passed through by guide vanes, referred to as IGV, for connecting the first and second envelopes, as well as by tubular arms of an inlet casing located downstream of the IGV,
the gas generator comprising a third annular envelope which coaxially surrounds the second envelope,
the second and third envelopes being connected together at their upstream ends to form an annular splitter nose for separating the primary and secondary flows.