Abstract: An annular intermediate casing for a turbomachine through which an aerodynamic airstream circulates, including a radially internal shroud (31), a radially external shroud, at least one stator blade including a vane with a leading edge, and at least one aero-dynamic member which is formed of a structural arm extending radially at least in part between the radially internal shroud and the radially external shroud. The aerodynamic member includes a leading edge which is aligned with the leading edge of the stator blade in one plane and which is borne by a profiled portion positioned upstream of the structural arm in the direction of circulation of the aerodynamic airstream, the profiled portion, the structural arm, the radially internal shroud and the radially external shroud being monobloc.

Abstract: The invention relates to an assembly for holding an epicyclic gear train in a turbomachine comprising an annular housing in which are engaged a first annular part and a second annular part which are locked against rotation in the housing by first annular interlocking means and second annular interlocking means, respectively, wherein the first annular interlocking means are configured to allow a first circumferential clearance between the first annular part and the housing, the second annular interlocking means are configured to allow a second circumferential clearance between the second annular part and the housing, and the first circumferential clearance is strictly less than the second circumferential clearance.

Abstract: An aircraft propulsion assembly including a fan shaft which is connected to a turbine shaft by means of a reduction gear. The guiding of the fan shaft is carried out by a first bearing including cylindrical rollers and a second beating including two rows of balls with oblique contact.

Abstract: The invention relates to an assembly for holding (42) an epicyclic gear train in a turbomachine comprising an annular housing (50) in which are engaged a first annular part (44) and a second annular part (46) which are locked against rotation in the housing (50) by first annular interlocking means and second annular interlocking means, respectively, wherein: the first annular interlocking means are configured to allow a first circumferential clearance between the first annular part (44) and the housing (50); the second annular interlocking means are configured to allow a second circumferential clearance between the second annular part (48) and the housing (50); the first circumferential clearance is strictly less than the second circumferential clearance.

Abstract: To facilitate the removal of a bearing housed in an arm of a turbomachine casing, which bearing guides a transmission shaft of the turbomachine, a casing arm includes a body with a vertical portion and a base defining a portion of a shaft housing; an additional part removably attached to the body and defining a bearing housing opening in the shaft housing; and a removable shim inserted between the base and the additional part. A turbomachine including such a casing arm is also described, as well as a method for removing the bearing from such a turbomachine, including removing the shim and moving the additional part towards the base, thereby allowing access to the bearing.

Abstract: A ring of vanes for an aircraft turbine engine, the ring presenting an axial direction and a radial direction and including a first annular sheath presenting an inside surface and a second annular sheath presenting an inside surface facing the first inside surface of the first annular sheath, the first and second sheaths being coaxial and defining between them a flow passage for a gas stream. The ring further includes both partially annular acoustic treatment panels including resonant cavities and also vanes extending in the radial direction between the first and second sheaths. Each vane includes a radial airfoil with at least two attachment tabs at each radial end of the airfoil fastened to the first or second sheath, and the inside surface of at least one of the first and second annular sheaths and the corresponding attachment tabs are covered by acoustic treatment panels arranged between the airfoils.

Abstract: A device for de-icing a splitter nose of an aviation turbine engine, the device including a splitter nose having an outer annular wall defining the inside of the bypass stream flow channel and an inner annular wall defining an inlet of the core stream flow channel, and an inner shroud mounted at its upstream end on the inner annular wall of the splitter nose and designed to have inlet guide vanes fastened thereto, the splitter nose and the inner shroud defining an annular volume. The device includes an annular deflector positioned inside the annular volume so as to subdivide the annular volume into a first annular cavity and a second annular cavity, the second annular cavity being defined between the annular deflector and the outer annular wall of the splitter nose.

Abstract: A ring of vanes for an aircraft turbine engine, the ring presenting an axial direction and a radial direction and including a first annular sheath presenting an inside surface and a second annular sheath presenting an inside surface facing the first inside surface of the first annular sheath, the first and second sheaths being coaxial and defining between them a flow passage for a gas stream. The ring further includes both partially annular acoustic treatment panels including resonant cavities and also vanes extending in the radial direction between the first and second sheaths. Each vane includes a radial airfoil with at least two attachment tabs at each radial end of the airfoil fastened to the first or second sheath, and the inside surface of at least one of the first and second annular sheaths and the corresponding attachment tabs are covered by acoustic treatment panels arranged between the airfoils.

Abstract: To facilitate the removal of a bearing housed in an arm of a turbomachine casing, which bearing guides a transmission shaft of the turbomachine, a casing arm includes a body with a vertical portion and a base defining a portion of a shaft housing; an additional part removably attached to the body and defining a bearing housing opening in the shaft housing; and a removable shim inserted between the base and the additional part. A turbomachine including such a casing arm is also described, as well as a method for removing the bearing from such a turbomachine, including removing the shim and moving the additional part towards the base, thereby allowing access to the bearing.

Abstract: A device for de-icing a splitter nose of an aviation turbine engine, the device including a splitter nose having an outer annular wall defining the inside of the bypass stream flow channel and an inner annular wall defining an inlet of the core stream flow channel, and an inner shroud mounted at its upstream end on the inner annular wall of the splitter nose and designed to have inlet guide vanes fastened thereto, the splitter nose and the inner shroud defining an annular volume. The device includes an annular deflector positioned inside the annular volume so as to subdivide the annular volume into a first annular cavity and a second annular cavity, the second annular cavity being defined between the annular deflector and the outer annular wall of the splitter nose.

Abstract: A method for mounting an acoustic panel on the inner surface of an annular housing of an axial turbomachine, the cylindrical acoustic panel comprising at least one longitudinal slot so as to define two opposing ends, the method comprising: bringing the two opposing ends closer together so as to reduce the cylinder radius of the acoustic panel; inserting the acoustic panel into the fan casing when the opposing ends are close together; deploying the opposing ends so as to increase the cylinder radius of the acoustic panel; and securing the acoustic panel to the housing by gluing.

Abstract: A coupling made of composite material including a polymer matrix reinforced by a fiber structure is disclosed. The coupling includes a structural portion reinforced by a main fiber structure, and a first machining portion reinforced by a first fiber structure that is distinct from the main fiber structure. The matrices of the structural portion and of the first machining portion are identical. The first machining portion is situated on at least a fraction of the main face of the structural portion and is machined in a first machining surface. There is no intersection between the first machining surface and the fibers of the main fiber structure.

Abstract: This invention relates to an assembly (100) for an aircraft turbofan comprising a flowpath splitter (40) downstream from which there is firstly a fan flowpath (31) inner delimitation ring (44) and secondly a compressor case (42), the assembly comprising a plurality of outlet guide vanes (34) provided with an inner platform (50) located in the downstream continuity of the delimitation ring. According to the invention, the assembly comprises at least one part (52) to support the delimitation ring (44), comprising a radially outer end (52b) fixed to a downstream part of this ring (44) and a radially inner end (52a) fixed to the compressor case (42).

Abstract: A rotor of a turbomachine, such as a multi-flow turbojet engine fan, has a disc including, on the rim thereof, substantially axial slots with a dovetailed cross-section, and blades mounted individually in the slots, an axial wedge positioned between the root of the blades and the bottom of the slots, and a transverse lock providing upstream axial immobilization of the blades in the slot thereof. The lock is guided in radial notches formed in the flanks of the slots and radially supported against the wedge. The axial wedge is immobilised in the upstream direction, butting up against a transverse annular component secured to the disc.

Abstract: A method for mounting an acoustic panel on the inner surface of an annular housing of an axial turbomachine, the cylindrical acoustic panel comprising at least one longitudinal slot so as to define two opposing ends, the method comprising: bringing the two opposing ends closer together so as to reduce the cylinder radius of the acoustic panel; inserting the acoustic panel into the fan casing when said opposing ends are close together; deploying the opposing ends so as to increase the cylinder radius of the acoustic panel; securing the acoustic panel to the housing by gluing.

Abstract: This invention relates to an assembly (100) for an aircraft turbofan comprising a flowpath splitter (40) downstream from which there is firstly a fan flowpath (31) inner delimitation ring (44) and secondly a compressor case (42), the assembly comprising a plurality of outlet guide vanes (34) provided with an inner platform (50) located in the downstream continuity of the delimitation ring. According to the invention, the assembly comprises at least one part (52) to support the delimitation ring (44), comprising a radially outer end (52b) fixed to a downstream part of this ring (44) and a radially inner end (52a) fixed to the compressor case (42).

Abstract: A rotor of a turbomachine, such as a multi-flow turbojet engine fan, has a disc including, on the rim thereof, substantially axial slots with a dovetailed cross-section, and blades mounted individually in the slots, an axial wedge positioned between the root of the blades and the bottom of the slots, and a transverse lock providing upstream axial immobilization of the blades in the slot thereof. The lock is guided in radial notches formed in the flanks of the slots and radially supported against the wedge. The axial wedge is immobilised in the upstream direction, butting up against a transverse annular component secured to the disc.

Abstract: A one-piece soundproofing panel which is attached within an circumferential air blower casing of a turbomachine, with an axis, in which circulates an airflow from upstream to downstream, is disclosed. The panel includes a circumferential rigid seat with a longitudinal cylindrical part, arranged to axially extend with respect to the axis A of the turbomachine, having an outside surface, intended to come to extend facing with an internal surface of the air blower casing, and an internal surface to which is applied a soundproofing coating; and an annular fastening flange, formed at the upstream end of the longitudinal cylindrical part, radially outwardly extending, the fastening flange being arranged to cooperate with a fastening flange of the air blower casing.

Abstract: A coupling made of composite material including a polymer matrix reinforced by a fiber structure is disclosed. The coupling includes a structural portion reinforced by a main fiber structure, and a first machining portion reinforced by a first fiber structure that is distinct from the main fiber structure. The matrices of the structural portion and of the first machining portion are identical. The first machining portion is situated on at least a fraction of the main face of the structural portion and is machined in a first machining surface, and there is no intersection between the first machining surface and the fibers of the main fiber structure.

Abstract: One-piece soundproofing panel intended to be attached within an circumferential air blower casing of a turbomachine, comprising an axis, in which circulates an airflow from upstream to downstream, the panel including a circumferential rigid seat comprising a longitudinal cylindrical part, arranged to axially extend with respect to the axis A of the turbomachine, comprising an outside surface, intended to come to extend facing with an internal surface of the air blower casing, and an internal surface to which is applied a soundproofing coating and an annular fastening flange, formed at the upstream end of the longitudinal cylindrical part, radially outwardly extending, the fastening flange being arranged to cooperate with a fastening flange of the air blower casing.