Abstract: The invention relates to a turbine engine separate flow mixer centered on a longitudinal axis, comprising an exhaust housing, a shroud directly connected to the exhaust housing and intended to mix the flows originating in the turbine engine, said shroud comprising a metal sheet formed by a succession of first and second longitudinal strips distributed circumferentially around the longitudinal axis of the mixer by circumferentially placing the second strips on either side of the first strips, the first and second strips being configured to form the shroud when at rest and grooves in the shroud when operating, the grooves being defined by an alternation of internal lobes and of external lobes.

Abstract: The invention relates to a device (100) for maintaining at least one cooling tube (T) outside a turbomachine casing (19), comprising: a support (1), comprising an inner face turned towards the tube (T) and at least one left tab (12) for partially retaining towards the left of the tube (T), located on the side of this inner face and fastened thereto, a support (2), comprising an inner face turned towards the tube (T) and at least one right tab (22) for partially retaining towards the right the tube (T), located on the side of this inner face and fastened thereto, means (13) for fastening the support (1) to a flange (BAM) of the casing (19), means (23) for fastening the support (2) to a flange (BAV) of the casing (19), distinct from the means (13).

Abstract: A sealing ring element of a turbomachine includes: a sealing portion with a first area and a second area, with the inner surface of a first area being at the same radial distance from the axis of the turbomachine. The sealing portion includes an annular cavity which opens into an inner surface of the second area and extends into the first area, the annular cavity defining an upstream lateral wall and/or a downstream lateral wall forming an angle which is strictly between 0 and 90°.

Abstract: A gas turbine engine includes a device for providing sealing between one rotor section and one stator section. The device includes a coating made of an abradable material attached to the stator section. The device further includes a lip on a portion of the rotor section. The lip is configured to form a seal with the abradable material. The gas turbine engine further includes passages for a gaseous fluid and means for blowing such gaseous fluid. The passages open into the rotor section provided with the lip, so that blown gaseous fluid can be present in a zone radially located between the coating and the lip.

Abstract: A casing of a turbine of a turbine engine includes an internal shroud, an external shroud extending around the internal shroud, and hollow arms connecting the external shroud to the internal shroud and each intended to receive a tubular auxiliary element, each hollow arm defining an inner housing connecting a first passage orifice passing through the internal shroud in the radial direction to a second passage orifice passing through the external shroud in the radial direction, and including an inner wall facing the inner housing. Each arm includes at least one protrusion on the inner wall of the arm protruding from the inner wall towards the inner housing and defining a constriction of the inner housing in a section plane orthogonal to the direction in which the arm extends.

Abstract: A casing of a turbine of a turbine engine includes an internal shroud, an external shroud extending around the internal shroud, and hollow arms connecting the external shroud to the internal shroud and each intended to receive a tubular auxiliary element, each hollow arm defining an inner housing connecting a first passage orifice passing through the internal shroud in the radial direction to a second passage orifice passing through the external shroud in the radial direction, and including an inner wall facing the inner housing. Each arm includes at least one protrusion on the inner wall of the arm protruding from the inner wall towards the inner housing and defining a constriction of the inner housing in a section plane orthogonal to the direction in which the arm extends.

Abstract: The invention relates to a turbine for a turbine engine, having a stator and a rotor comprising a rotor wheel having vanes the radially external periphery of which comprises at least one lip which radially extends outwards, with sealing means radially extending about the vanes and comprising a ring. The radially external end of the lip cooperates with said ring so as to form a seal of the labyrinth type.

Abstract: The invention relates to a device (100) for maintaining at least one cooling tube (T) outside a turbomachine casing (19), comprising: a support (1), comprising an inner face turned towards the tube (T) and at least one left tab (12) for partially retaining towards the left of the tube (T), located on the side of this inner face and fastened thereto, a support (2), comprising an inner face turned towards the tube (T) and at least one right tab (22) for partially retaining towards the right the tube (T), located on the side of this inner face and fastened thereto, means (13) for fastening the support (1) to a flange (BAM) of the casing (19), means (23) for fastening the support (2) to a flange (BAV) of the casing (19), distinct from the means (13).

Abstract: A turbine for a turbine engine, the turbine comprising a rotor including blades the radially external periphery of which includes at least one first wiper radially extending outwards, sealing means radially extending about the blades and including a ring made of abradable material, with the radially external ends of the wipers cooperating with said ring made of abradable material so as to form a labyrinth-type seal, wherein said ring includes at least one first portion axially extending upstream of the first wiper and a second portion, different from the first portion, axially extending downstream of the first wiper, with the first portion and/or the second portion including a groove, wherein the first wiper has been inserted, with said groove being defined by the first portion and by the second portion.

Abstract: The invention relates to a turbine for a turbine engine, having a stator and a rotor comprising a rotor wheel having vanes the radially external periphery of which comprises at least one lip which radially extends outwards, with sealing means radially extending about the vanes and comprising a ring. The radially external end of the lip cooperates with said ring so as to form a seal of the labyrinth type.

Abstract: A gas turbine engine includes a device for providing sealing between one rotor section and one stator section. The device includes a coating made of an abradable material attached to the stator section. The device further includes a lip on a portion of the rotor section. The lip is configured to form a seal with the abradable material. The gas turbine engine further includes passages for a gaseous fluid and means for blowing such gaseous fluid. The passages open into the rotor section provided with the lip, so that blown gaseous fluid can be present in a zone radially located between the coating and the lip.

Abstract: The main object of the invention is a sealing ring element (6s) of a turbomachine, comprising a sealing portion (6p) with a first area (6p1) and a second area (6p2), with the inner surface (6i) of a first area (6p1) being at the same radial distance from the axis (X) of the turbomachine, characterised in that the sealing portion (6p) comprises an annular cavity (6c) which opens into an inner surface of the second area (6p2) and extends into the first area (6p1), the annular cavity (6c) defining an upstream lateral wall (6m) and/or a downstream lateral wall (6v) forming an angle (?) which is strictly between 0 and 90°.

Abstract: A turbine for a turbine engine, the turbine comprising a rotor including blades the radially external periphery of which includes at least one first wiper radially extending outwards, sealing means radially extending about the blades and including a ring made of abradable material, with the radially external ends of the wipers cooperating with said ring made of abradable material so as to form a labyrinth-type seal, wherein said ring includes at least one first portion axially extending upstream of the first wiper and a second portion, different from the first portion, axially extending downstream of the first wiper, with the first portion and/or the second portion including a groove, wherein the first wiper has been inserted, with said groove being defined by the first portion and by the second portion.