Abstract: A hybrid turbofan engine for an aircraft, comprising a fan, an electric motor/generator and a gas generator, the engine comprising, between the fan and a splitter that separates the flows, an internal wall for delimiting an air duct, situated upstream of inlet guide vanes of a primary duct, and, upstream of outlet guide vanes, an internal upstream wall for delimiting a secondary duct, the motor/generator having a stator carried by a stator support fixed to a stator part of the engine. According to the invention, a plurality of heat pipe for cooling the motor/generator are provided, each heat pipe having an evaporation section fixed to the stator support, and a condensation section fixed to the internal wall or the internal upstream wall.

Abstract: Disclosed is an electrically conductive rigid bar (80) for electrically connecting an electric machine (70) of an aircraft turbine engine, characterised in that it comprises: —an elongate body (80a) made from electrically conductive material having a polygonal cross-section greater than or equal to 50 mm2, and— an electrical insulation sheath (80b) that surrounds the body, at least one of the longitudinal ends (84a) of the body not being covered by the sheath and comprising a through-hole (86) in which a bolt (88) for fastening and electrically connecting this end is mounted.

Abstract: An aircraft turbine engine including a gas generator, a fan, and an electrical machine, the stator of the electrical machine being connected to a power electronic circuit by at least one electrically conductive bar which extends substantially radially relative to the axis inside an IGV which forms part of a bladed angular segment, the bar being configured to be disassembled and removed from the turbine engine by disassembling and removing the segment.

Abstract: An aircraft turbine engine includes a gas generator having a longitudinal axis (A), a fan which is located at an upstream end of the gas generator and which is configured to rotate about the axis, and an electric machine which has a generally annular shape. The electric machine is mounted coaxially downstream of the fan and has a rotor which is coupled in terms of rotation to the fan, and a stator which is connected to an electronic power circuit by at least one rigid electroconductive bar.

Abstract: The invention relates to a blade pivot with adjustable orientation for a turbomachine fan hub, comprising: a stud having a fastener configured to retain a blade root and coupling means for the transmission of a twist torque; a ball bearing for taking centrifugal forces having an inner ring and an outer ring; a first clamping nut intended to be screwed on an inner thread of the hub to ensure clamping of the outer ring of the ball bearing; a rolling-element bearing for taking transverse forces having an inner ring and a smooth outer ring; a locking ring mounted between these two inner rings to provide for them a respective transverse support; an anti-rupture sleeve carrying the inner ring of the rolling-element bearing for taking transverse forces and the terminal end of which is extended transversely beyond the outer ring of this bearing.

Abstract: An aircraft turbine engine includes a gas generator and a fan arranged upstream from the gas generator and configured to generate a main gas flow, one portion of which flows in a flow path of the gas generator to form a primary flow, and another portion of which flows in a flow path around the gas generator to form a secondary flow. The gas generator includes a low-pressure compressor that includes a rotor driving the fan. The turbine engine further includes an electric machine. The electric machine includes a rotor rotated by the rotor of the low-pressure compressor, and a stator extending around the rotor of the electric machine and configured to be cooled by the primary flow.

Abstract: A fan module for an aircraft turbine engine, this module comprising a fan and an electrical machine, such that the electrical machine is coaxially mounted downstream of the fan and comprises a rotor coupled to rotate with the fan and an annular member with generally C-shaped axial cross-section, the opening of which is axially orientated and receives the rotor, this member comprising a radially outer portion forming a stator, and a radially inner portion forming a support for bearings guiding the rotor.

Abstract: An aircraft turbine engine includes a gas generator and a fan arranged upstream of the gas generator and configured to generate a main gas flow, of which one portion flows in a stream from the gas generator to form a primary flow, and of which another portion flows in a stream around the gas generator to form a secondary flow. The gas generator includes a low pressure body having a rotor driving the fan by means of a crown of a mechanical planetary reduction gear. The turbine engine further includes an electrical machine mounted coaxially around the reduction gear and having a rotor rotated by the crown of the reduction gear, and a stator extending around the rotor of the electrical machine.

Abstract: The invention relates to a blade pivot with adjustable orientation for a turbomachine fan hub, comprising: a stud having a fastener configured to retain a blade root and coupling means for the transmission of a twist torque; a ball bearing for taking centrifugal forces having an inner ring and an outer ring; a first clamping nut intended to be screwed on an inner thread of the hub to ensure clamping of the outer ring of the ball bearing; a rolling-element bearing for taking transverse forces having an inner ring and a smooth outer ring; a locking ring mounted between these two inner rings to provide for them a respective transverse support; an anti-rupture sleeve carrying the inner ring of the rolling-element bearing for taking transverse forces and the terminal end of which is extended transversely beyond the outer ring of this bearing.

Abstract: An aircraft turbomachine, including a fan that is able to rotate inside a casing, and an electric machine including a rotor secured to the fan and a stator secured to the casing, wherein the rotor of the electric machine includes a ring that is able to rotate inside the stator, which is linked by arms to a cone mounted upstream from the fan.

Abstract: A blade pivot of adjustable orientation for a turbomachine fan hub includes: a block having a retaining device configured to retain a fan blade root and a coupling device for the transmission of a torque; a ball type rolling bearing for taking up centrifugal forces having an inner ring; a clamping nut screwed onto an external thread of the block in order to clamp the inner ring of the ball type rolling bearing for taking up centrifugal forces to the block; a rolling bearing for taking up transverse forces; a pitch setting transmission ring positioned inside the inner radial end of the block and equipped with a coupling device cooperating with the coupling device of the block, and a device for locking the pitch setting transmission ring on the block.

Abstract: An electric module of a fan includes a fan provided with blades which are rotatably movable inside a casing, and an electric machine having a rotor secured to the fan and a stator integrated into said casing. The rotor of the electric machine is integrated into the fan and includes a removable ring which captures axially and transversely from the radially outer ends the blades of the fan and which is received inside said stator which is integrated into the casing.

Abstract: The invention relates to a blade pivot with adjustable orientation for a turbomachine fan hub, comprising a stud having means for retaining a fan blade root and coupling means for the transmission of a torsional torque, a rolling bearing for absorbing the centrifugal forces having an inner bushing mounted in transverse abutment against an external radial portion of the stud, a ring for radially retaining the stud relative to the rolling bearing housed in an annular groove formed in the stud, a plurality of clamping parts each mounted in transverse abutment against the retaining ring and in radial abutment against the inner bushing of the rolling bearing, and a clamping nut screwed onto an outer thread of the stud to come into conical abutment against the clamping parts such that said clamping parts ensure a clamping of the inner bushing of the rolling bearing on the stud and a clamping

Abstract: Disclosed is an electrically conductive rigid bar (80) for electrically connecting an electric machine (70) of an aircraft turbine engine, characterised in that it comprises:- an elongate body (80a) made from electrically conductive material having a polygonal cross-section greater than or equal to 50 mm2, and - an electrical insulation sheath (80b) that surrounds the body, at least one of the longitudinal ends (84a) of the body not being covered by the sheath and comprising a through-hole (86) in which a bolt (88) for fastening and electrically connecting this end is mounted.

Abstract: An aircraft turbine engine includes a gas generator having a longitudinal axis (A), a fan which is located at an upstream end of the gas generator and which is configured to rotate about the axis, and an electric machine which has a generally annular shape. The electric machine is mounted coaxially downstream of the fan and has a rotor which is coupled in terms of rotation to the fan, and a stator which is connected to an electronic power circuit by at least one rigid electroconductive bar.

Abstract: A device (26) for cooling an annular outer turbine casing (17) includes at least one circumferentially extending tube (27) having an air inlet intended for conveying cooling air, the tube having a radially inner wall provided with cooling air discharge openings and a radially outer wall arranged radially opposite each other, an air inlet manifold (28), the inlet of the tube opening into the manifold, the tube (27) including at least one intermediate wall extending over a circumferential portion of the tube from the air inlet, the intermediate wall being located radially between the radially inner wall and the radially outer wall, the radially inner wall and the intermediate wall forming a first air conveying duct, the radially outer wall and the intermediate wall forming a second air conveying duct extending circumferentially beyond the first air conveying duct, relative to the air inlet.

Abstract: An aircraft turbine engine includes a gas generator having a longitudinal axis (A), a fan located at an upstream end of the gas generator and configured to turn about said axis, and an electric machine of generally annular shape. The electric machine is coaxially mounted downstream of the fan and has a rotor coupled to rotate with the fan. The electric machine further includes a stator connected to an electronic power circuit by at least one rigid electrically-conductive bar.

Abstract: An electric module for an aircraft turbomachine includes an electric machine stator having an annular shape around an axis (A) and being configured to surround a rotor of the electric machine, and an annular support element of the stator. The support element includes an outer annular surface configured to be swept over by a gas stream (F) from the turbomachine with a view to conductively cooling the stator.

Abstract: The invention relates to a lubrication device (1) for a turbo machine, comprising: a rotor (2) rotating around an axis, at least one lubrication chamber (6) formed in the rotor (2), a stator (22) in which the rotor (2) is rotatably mounted, a bearing (11) for rotationally guiding the rotor (2), mounted between the rotor (2) and the stator, lubricating fluid supply means which supply at least the chamber (6) and the bearing (11), the lubricating fluid supply means comprising a nozzle (23) mounted on the stator provided with an ejection nozzle (34) at a free end of the nozzle (23), said nozzle (34) being configured to project the lubricating fluid into the chamber (6), characterized in that the nozzle (23) has a movable part (27) including said ejection nozzle (34), said movable part (27) being movable between a retracted position in which the ejection nozzle (34) is remote from the chamber (6) or at least partially located outside the chamber (6), and an extended position in which the nozzle (34) is closer

Abstract: An aircraft turbine engine includes a low-pressure body and a high-pressure body, as well as means for drawing power on said low-pressure body, said means having a first shaft for drawing power, the radially inner end of said first shaft bearing a first bevel gear meshed with a first idler bevel wheel driven by the low-pressure body, the turbine engine further having a first annular bearing support which extends about an axis and is rigidly connected to a stator. The first bearing support includes a first cylindrical portion which extends coaxially with a second substantially cylindrical portion of the idler wheel, said first and second portions being guided one inside the other by bearings, and the idler wheel is driven by the low-pressure body by means of an annular damping piece which is independent of the first bearing support.