Abstract: An assembly for a turbine of a turbine engine, including a casing and an annular duct surrounding the casing, which can be connected to a device for supplying cooling air, and having a radially inner annular wall provided with openings arranged opposite the casing in order to cool same by the impact of cooling-air jets. The casing has a plurality of axial grooves including first grooves and second grooves arranged in alternation, and the openings are distributed in a plurality of annular rows in which any pair of consecutive annular rows is such that the openings of one of the annular rows of the pair are centered relative to the first grooves while the openings of the other annular row of the pair are centered relative to the second grooves.

Abstract: Disclosed is a movable vane (1) for a wheel (2) of an aircraft turbine engine, the vane (1) comprising a blade (4) delimited by an outer heel (8) comprising a first seal (14), the vane (1) comprising an internal circuit (16) suitable for receiving a first minor gas flow (f1), this circuit (16) comprising a supply cavity (17) opening at the root (9) via at least one inlet opening (18), characterised in that the circuit (16) comprises at least two channels (19) connected with the supply cavity (17) and each opening on an outer surface of the first seal (14) via a discharge opening such that a gas jet (J) of the first minor gas flow (f1) is capable of being discharged from each discharge opening, each channel (19) being oriented such that the corresponding gas jet (J) is capable of being projected towards a second minor gas flow (f2) escaping between the heel (8) and a directly adjacent member (22).

Abstract: A cooling device for an annular casing of a turbomachine includes a collector housing having ejection openings in a radially inner part of the collector housing facing the annular casing and at least two cooling tubes extending circumferentially from the collector housing and having election openings in a radially inner part of the tubes facing the annular casing. The collector housing having an air passage formed by a radial groove extending radially from a radially inner end of the collector housing to a radially outer end of the collector housing and an axial groove extending from a first axial end to a second axial end of the collector housing.

Abstract: The invention relates to a ring (1) for a turbomachine turbine or a turboshaft engine turbine, intended to surround an impeller (2) of a turbine rotor, the said ring (1) extending circumferentially about an axis and comprising an annular and continuous support part (9), radially external, and a part (10) delimiting a circulation passage (6) of a gas flow, radially internal and comprising a plurality of angular segments (13) distributed over the periphery and situated adjacent to one another so as to form an annular part delimiting the passage (6), characterised in that circumferential clearances (j) are formed between the circumferential ends of the adjacent segments (13) located opposite each other, each segment (13) being connected to the support part (9) by means of a connecting zone (14), an annular channel (15) for the circulation of cooling fluid being delimited radially between the outer support part (9) and the inner part (10) delimiting the passage.

Abstract: A device for controlling the clearance between a rotor and a stator surrounding same, which is carried out by modifying the delivery flow carried in a rotor recess in order to provide a bleed flow that prevents the gases from the flow section from penetrating into the recess. A valve can partially close the delivery circuit, thus reducing the cooling of the rotor structure and allowing the expansion thereof and the reduction of the clearance with the stator, for certain operating speeds including cruise operating speeds. In addition, the delivery air is heated more at a lower flow rate, especially if it is made to follow a bypass provided with meanders in the hottest portions of the circuit.

Abstract: A labyrinth seal lip (5) comprises, standing on one of its lateral faces (7), a deflector (13) which channels the flow of gas tangent to the lip (5) towards the facing seal (4) so as to disturb the leakage flow (22) through the gap and decrease the flow rate.

Abstract: The invention relates to a device (21) for cooling an annular casing (18) of a turbomachine, comprising a collector housing (22) intended to extend circumferentially around the axis of the casing (18), at least two cooling tubes (23) extending circumferentially and connected to the internal volume of the housing (22), the housing (22) and/or each tube (23) having ejection openings opening radially towards the casing (18), characterised in that connecting portions of the tubes (23) formed in one piece with the housing (22) extend circumferentially projecting from the housing (22), forming between them at least one recessed area (29) of the housing which allows an air passage radially from the inside to the outside of the housing (22).

Abstract: A turbo engine rotor disc that has a rotation axis and includes, at the periphery thereof, a plurality of slots regularly distributed around the rotation axis, wherein at least one slot of the plurality of slots has a base that has a plurality of plates arranged in staggered rows and protruding from the base, each plate extending mainly along a direction perpendicular to a radial direction.

Abstract: A labyrinth seal lip (5) comprises, standing on one of its lateral faces (7), a deflector (13) which channels the flow of gas tangent to the lip (5) towards the facing seal (4) so as to disturb the leakage flow (22) through the gap and decrease the flow rate.

Abstract: A tubular shaft (8) of a turbomachine, including at the inner periphery of same, a bath (11), substantially perpendicular to splines (9), the bath (11) includes cavities (17) distributed over a circumference centred on an axis of rotation (LL) of the shaft (8).

Abstract: A device for controlling the clearance between a rotor and a stator surrounding same, which is carried out by modifying the delivery flow carried in a rotor recess in order to provide a bleed flow that prevents the gases from the flow section from penetrating into the recess. A valve can partially close the delivery circuit, thus reducing the cooling of the rotor structure and allowing the expansion thereof and the reduction of the clearance with the stator, for certain operating speeds including cruise operating speeds. In addition, the delivery air is heated more at a lower flow rate, especially if it is made to follow a bypass provided with meanders in the hottest portions of the circuit.

Abstract: The invention relates to a ventilation device for a turbomachine turbine casing, comprising a plurality of line sets (16?) configured to spray air over the turbine casing, the line sets being arranged next to one another, each line set comprising a main ring (161) in which air circulates, the main ring (161) comprising orifices (17?) configured to spray a stream of air towards the turbine casing, the line set comprising a shield (162) configured to isolate the main ring (161) from a stream of air returning from the turbine casing towards the line sets after having been sprayed towards the turbine casing, the said shield (162) enveloping the main ring (161) and having orifices aligned with the orifices of the main ring (161).

Abstract: The invention relates to an exhaust casing for a turbine engine of an aircraft, including: a collar (4), a hub (5), hollow arms (63) connecting said collar (4) to said hub (5), and an opening piece (3) which is located on the collar (4) and is suitable for being connected to an outlet tube (30) of a transient-operation valve of the turbine engine. In said exhaust casing, said opening piece (3) is attached onto the collar (4) and forms an extension of a hollow arm (63) such that an air flow (7) leaving the outlet tube (30) of the transient-operation valve penetrates the hollow arm (63) and flows into the hub (5).

Abstract: A turbo engine rotor disc that has a rotation axis and includes, at the periphery thereof, a plurality of slots regularly distributed around the rotation axis, wherein at least one slot of the plurality of slots has a base that has a plurality of plates arranged in staggered rows and protruding from the base, each plate extending mainly along a direction perpendicular to a radial direction.

Abstract: The invention relates to a ventilation device for a turbomachine turbine casing, comprising a plurality of line sets (16?) configured to spray air over the turbine casing, the line sets being arranged next to one another, each line set comprising a main ring (161) in which air circulates, the main ring (161) comprising orifices (17?) configured to spray a stream of air towards the turbine casing, the line set comprising a shield (162) configured to isolate the main ring (161) from a stream of air returning from the turbine casing towards the line sets after having been sprayed towards the turbine casing, the said shield (162) enveloping the main ring (161) and having orifices aligned with the orifices of the main ring (161).

Abstract: An assembly for a turbine of a turbine engine, including a casing and an annular duct surrounding the casing, which can be connected to a device for supplying cooling air, and having a radially inner annular wall provided with openings arranged opposite the casing in order to cool same by the impact of cooling-air jets. The casing has a plurality of axial grooves including first grooves and second grooves arranged in alternation, and the openings are distributed in a plurality of annular rows in which any pair of consecutive annular rows is such that the openings of one of the annular rows of the pair are centered relative to the first grooves while the openings of the other annular row of the pair are centered relative to the second grooves.

Abstract: The invention relates to an exhaust casing for a turbine engine of an aircraft, including: a collar (4), a hub (5), hollow arms (63) connecting said collar (4) to said hub (5), and an opening piece (3) which is located on the collar (4) and is suitable for being connected to an outlet tube (30) of a transient-operation valve of the turbine engine. In said exhaust casing, said opening piece (3) is attached onto the collar (4) and forms an extension of a hollow arm (63) such that an air flow (7) leaving the outlet tube (30) of the transient-operation valve penetrates the hollow arm (63) and flows into the hub (5).

Abstract: The invention concerns a tubular shaft (8) of a turbomachine, comprising, at the inner periphery of same, a bath (11), substantially perpendicular to said splines (9), characterised in that said bath (11) comprises cavities (17) distributed over a circumference centred on the axis of rotation (LL) of the shaft (8). The invention also concerns an assembly comprising said turbomachine shaft, a turbomachine and a method for detecting an oil imbalance.