Abstract: An assembly for a turbomachine through which an air flow passes, includes a stator including guide vanes extending radially in relation to a longitudinal axis, at least one inter-vane platform extending between the radially outer ends of two circumferentially consecutive guide vanes, each inter-vane platform including an outer surface that faces the axis, a heat exchanger located downstream of the stator in relation to a direction of circulation of the air flow in the turbomachine during operation, this stator including a heat exchange surface extending in the extension of an inter-vane platform. At least one inter-vane platform located in the upstream extension of the heat exchange surface is provided with at least one turbulence generator on its outer surface.

Abstract: A sealing assembly (1) for a turbine engine comprising a first element (2) and a second element (3), the first and second elements (2, 3) being concentric and in relative rotational movement with respect to each other about an axis of rotation (X), the sealing assembly (1) comprising at least one first wiper (4a) and an abradable member (5), the first wiper (4a) being annular in shape and carried by the first element (2), the first wiper (4a) extending radially towards the abradable member (5) and continuously around the axis of rotation (X), the abradable member (5) being annular in shape and carried by the second element (3), the abradable member (5) extending tangentially opposite the first wiper (4a), the first wiper (4a) comprising primary angular portions (11), each extending tangentially along a primary angular sector (11?), the primary angular portions (11) each having, in cross-section, a first constant profile, characterised in that the first wiper (4a) comprises secondary angular portions (13) each

Abstract: The invention relates to an assembly for a turbomachine, comprising a stator (1) and a rotor (2) rotatable relative to the stator (1) about an axis, the rotor (2) comprising blades each ×comprising a vane (3) connected to a radially inner platform (5), a block of abradable material (6) extending radially inwardly from the radially inner platform (5) the stator (1) having a shroud comprising an annular area (9), at least one lug (12) extending radially outwardly from said annular area (9), the radially outer end of the lug (12) cooperating with the block of abradable material (6).

Abstract: An assembly for a turbomachine through which an air flow passes, includes a stator including guide vanes extending radially in relation to a longitudinal axis, at least one inter-vane platform extending between the radially outer ends of two circumferentially consecutive guide vanes, each inter-vane platform including an outer surface that faces the axis, a heat exchanger located downstream of the stator in relation to a direction of circulation of the air flow in the turbomachine during operation, this stator including a heat exchange surface extending in the extension of an inter-vane platform. At least one inter-vane platform located in the upstream extension of the heat exchange surface is provided with at least one turbulence generator on its outer surface.

Abstract: A heat exchanger between a fluid and an air flow, includes a heat exchange wall separating the fluid and the air flow, the heat exchange wall including a heat exchange surface that extends parallel to a longitudinal direction of the air flow and with which the air flow is in contact. The heat exchange wall includes at least one turbulence generator extending in a hollow manner in relation to the heat exchange surface.

Abstract: The invention relates to an assembly for a turbomachine, comprising a stator (1) and a rotor (2) rotatable relative to the stator (1) about an axis, the rotor (2) comprising blades each comprising a vane (3) connected to a radially inner platform (5), a block of abradable material (6) extending radially inwardly from the radially inner platform (5) the stator (1) having a shroud comprising an annular area (9), at least one lug (12) extending radially outwardly from said annular area (9), the radially outer end of the lug (12) cooperating with the block of abradable material (6).

Abstract: An abradable element (7) for a turbomachine comprises a body (8) formed from an abradable material and extending between a wear face (11) and a bottom (9). The body comprises blind cavities (12) opening up into the wear face and filled in with a material with a colour different from the colour of the material forming the body of the element (7) to form wear indicators of the wear face (11) of the element (7).

Abstract: An angular sector of a fixed blading ring of a turbomachine, in particular of a stator or distributor, extends through a given angle about an axis A of the ring. The angular sector includes, with respect to axis A, a radially outer platform, a radially inner platform, at least two blades extending between the platforms, and at least one block of abradable honeycomb material. The abradable honeycomb material extends inwardly with respect to the inner platform between transverse ends of the sector and that comprises includes radially oriented tubular cells, in which the block of abradable material has at least one transverse end wall at which all of the cells are open by openings oriented away from the sector.

Abstract: Assembly forming a labyrinth seal for a turbomachine, comprising: at least one abradable material of which the inner surface defines a stair shape with a sequence of treads and risers; a plurality of fins extending radially toward said inner surface, the fins each comprising, at least in part, an upstream side wall forming a riser facing the corresponding fin such that, when seen in axial cross-section, the tangent at the top of the upstream side wall of at least one fin and the straight line passing through the downstream side wall of said at least one abradable material intersect, the angle between said tangent and said straight line being strictly between 5 and 15°.

Abstract: An abradable element (7) for a turbomachine comprises a body (8) formed from an abradable material and extending between a wear face (11) and a bottom (9). The body comprises blind cavities (12) opening up into the wear face and filled in with a material with a colour different from the colour of the material forming the body of the element (7) to form wear indicators of the wear face (11) of the element (7).

Abstract: A deicer device deices both a splitter nose and inlet guide vanes of an aviation turbine engine. The device includes a splitter nose to split a stream coming from the fan into primary and secondary stream flow channels of annular shape and an inner shroud to which inlet guide vanes are fastened and including a hook that holds the inner shroud axially at its upstream end against the inner annular wall. An outer surface facing of the hook forms an angle of less than 90° with an injection orifice such that the outer surface comes progressively closer to the outer annular wall on going away from the injection orifice. The outer surface of the hook presents a minimum amount of clearance J relative to the outer annular wall such that 0.2?J/D?0.6 where D is the hydraulic diameter of an injection orifice.

Abstract: An anti-icing system for a turbine engine vane extending between an outer casing and an inner casing defining a passage, the system includes an injector device for injecting a jet of air into the passage upstream from the vane, the injector device including a first injection orifice for injecting the jet of air, the first orifice passing through one member selected from the outer casing and the inner casing, and being located in such a manner that, at a first speed of the engine wherein a stream of air flows generally in the passage along a first direction, the first orifice and a leading edge of the vane are substantially in alignment along the first direction, the first orifice is spaced apart from the junction between the leading edge of the vane and the member through which the first orifice passes by a distance of at least 10 mm, and preferably of about 15 mm.

Abstract: The main object of the invention is an angular stator sector (10) for a turbomachine compressor, comprising an outer shroud and an inner shroud (S) arranged coaxially one inside the other, and at least one vane (P) extending radially between the outer shroud and the inner shroud (S) and connected to the latter by its radial ends, characterized in that the inner shroud (S) comprises at least one brush seal (1, 2, 3) forming an obstacle to the recirculation of the downstream gases upstream of the inner shroud (S).

Abstract: Assembly forming a labyrinth seal for a turbomachine, comprising: at least one abradable material of which the inner surface defines a stair shape with a sequence of treads and risers; a plurality of fins extending radially toward said inner surface, the fins each comprising, at least in part, an upstream side wall forming a riser facing the corresponding fin such that, when seen in axial cross-section, the tangent at the top of the upstream side wall of at least one fin and the straight line passing through the downstream side wall of said at least one abradable material intersect, the angle between said tangent and said straight line being strictly between 5 and 15°.

Abstract: A compressor shroud for an aircraft turbine engine, the shroud being arranged between two bladed rotary wheels and radially in line with a deflector, the shroud including a sealing device including one or more sealing elements, including a downstream end sealing element on which, projecting downstream, an air entraining and diverting structure is provided, designed to axially divert the discharge air issuing from the end sealing element.

Abstract: A deicer device deices both a splitter nose and inlet guide vanes of an aviation turbine engine. The device includes a splitter nose to split a stream coming from the fan into primary and secondary stream flow channels of annular shape and an inner shroud to which inlet guide vanes are fastened and including a hook that holds the inner shroud axially at its upstream end against the inner annular wall. An outer surface facing of the hook forms an angle of less than 90° with an injection orifice such that the outer surface comes progressively closer to the outer annular wall on going away from the injection orifice. The outer surface of the hook presents a minimum amount of clearance J relative to the outer annular wall such that 0.2?J/D?0.6 where D is the hydraulic diameter of an injection orifice.

Abstract: An anti-icing system for a turbine engine vane extending between an outer casing and an inner casing defining a passage, the system includes an injector device for injecting a jet of air into the passage upstream from the vane, the injector device including a first injection orifice for injecting the jet of air, the first orifice passing through one member selected from the outer casing and the inner casing, and being located in such a manner that, at a first speed of the engine wherein a stream of air flows generally in the passage along a first direction, the first orifice and a leading edge of the vane are substantially in alignment along the first direction, the first orifice is spaced apart from the junction between the leading edge of the vane and the member through which the first orifice passes by a distance of at least 10 mm, and preferably of about 15 mm.

Abstract: A compressor shroud for an aircraft turbine engine, the shroud being arranged between two bladed rotary wheels and radially in line with a deflector, the shroud including a sealing device including one or more sealing elements, including a downstream end sealing element on which, projecting downstream, an air entraining and diverting structure is provided, designed to axially divert the discharge air issuing from the end sealing element.

Abstract: A sealing device for an enclosure of a turbine engine formed by an assembly of juxtaposed rotating and/or static bodies is provided. The sealing device includes at least one brush seal having a brush body, carried by at least one first member, and bristles extending from the brush body and arranged so as to rub against at least one second member rotatable relative to the first member, so as to produce a pressure difference between the inside of said enclosure and its outer environment. The device further includes a labyrinth-type seal, the labyrinth being positioned in series with the brush seal between the inside of the enclosure and its outer environment.

Abstract: The main object of the invention is an angular stator sector (10) for a turbomachine compressor, comprising an outer shroud and an inner shroud (S) arranged coaxially one inside the other, and at least one vane (P) extending radially between the outer shroud and the inner shroud (S) and connected to the latter by its radial ends, characterised in that the inner shroud (S) comprises at least one brush seal (1, 2, 3) forming an obstacle to the recirculation of the downstream gases upstream of the inner shroud (S).