An aircraft turbine engine, 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 electrical machine of generally annular shape which is mounted coaxially downstream of the fan, and which comprises a rotor coupled in rotation to the fan, and a stator, 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 (37a, 37b) coaxial with the gas generator, the primary duct being passed through by bladings, referred to as IGV (52, 52a), 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 (37b, 39) being connected together at their upstream ends to form an annular splitter nose for separating the primary and secondary flows (36, 38), the stator of the electrical machine being connected to a power electronic circuit by at least one electrically conductive bar which extends substantially radially with respect to said axis inside one of the IGV, characterised in that said first and second envelopes (37a, 37b) are sectorised, each of the sectors of the first envelope being connected by IGV (52, 52a) to one of the sectors of the second envelope, to form bladed angular segments (G1, G2), only a portion of these segments comprising an IGV passed through by said at least one bar which is rigidly connected to that IGV and to that segment and which is configured to be disassembled and removed from the turbine engine by disassembly and removal of that segment. - 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 electrical machine of generally annular shape which is mounted coaxially downstream of the fan, and which comprises a rotor coupled in rotation to the fan, and a stator, 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 (37a, 37b) coaxial with the gas generator, the primary duct being passed through by bladings, referred to as IGV (52, 52a), 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 (37b, 39) being connected together at their upstream ends to form an annular splitter nose for separating the primary and secondary flows (36, 38), the stator of the electrical machine being connected to a power electronic circuit by at least one electrically conductive bar which extends substantially radially with respect to said axis inside one of the IGV, characterised in that said first and second envelopes (37a, 37b) are sectorised, each of the sectors of the first envelope being connected by IGV (52, 52a) to one of the sectors of the second envelope, to form bladed angular segments (G1, G2), only a portion of these segments comprising an IGV passed through by said at least one bar which is rigidly connected to that IGV and to that segment and which is configured to be disassembled and removed from the turbine engine by disassembly and removal of that segment. 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 (37a, 37b) coaxial with the gas generator, the primary duct being passed through by bladings, referred to as IGV (52, 52a), 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 (37b, 39) being connected together at their upstream ends to form an annular splitter nose for separating the primary and secondary flows (36, 38), the stator of the electrical machine being connected to a power electronic circuit by at least one electrically conductive bar which extends substantially radially with respect to said axis inside one of the IGV, characterised in that said first and second envelopes (37a, 37b) are sectorised, each of the sectors of the first envelope being connected by IGV (52, 52a) to one of the sectors of the second envelope, to form bladed angular segments (G1, G2), only a portion of these segments comprising an IGV passed through by said at least one bar which is rigidly connected to that IGV and to that segment and which is configured to be disassembled and removed from the turbine engine by disassembly and removal of that segment.