Abstract: A turbine of a gas turbine engine comprising a stator sealing ring element arranged so as to form a labyrinth sealing joint in combination with at least one wiper, rotatable about the axis of the sealing ring. The element includes an abradable material layer with a surface portion engageable with said movable wiper. The abradable material layer on the surface portion axially includes a first area having a first wiper penetration resistance, said first area corresponding to the axial position of the wiper during nominal operation of the turbine, and a second area adjacent to the first area and having lower wiper penetration resistance than the first area. The second area is located downstream from the first area and corresponds to the axial position that the wiper takes when a flame goes out in the combustion chamber of the engine.

Abstract: A turbine of a gas turbine engine comprising a stator sealing ring element arranged so as to form a labyrinth sealing joint in combination with at least one wiper, rotatable about the axis of the sealing ring. The element includes an abradable material layer with a surface portion engageable with said movable wiper. The abradable material layer on the surface portion axially includes a first area having a first wiper penetration resistance, said first area corresponding to the axial position of the wiper during nominal operation of the turbine, and a second area adjacent to the first area) and having lower wiper penetration resistance than the first area. The second area is located downstream from the first area and corresponds to the axial position that the wiper takes when a flame goes out in the combustion chamber of the engine.

Abstract: A cooling device for the casing of a jet engine, includes a cooling tube and a supporting device, the supporting device including an attachment plate and an attachment clamp, the attachment clamp including a clamp body surrounding the cooling tube and an attachment element attached to the attachment plate, wherein the attachment plate includes: an opening; and an attachment tab secured to the main wall of the attachment plate and arranged on at one portion of the periphery of the opening, the attachment clamp passing through the opening, and the attachment element of the attachment clamp being attached to the attachment tab.

Abstract: An interface device between first and second turbomachine elements is provided. The interface device includes an annular air inlet structure including opposite first and second parts, designed to come into contact with the first and second turbomachine elements respectively, in which the first part is configured to be in swivel contact with the first element; and an elastic return device that can be placed around the air inlet structure and designed to come into contact with at least the first turbomachine element.

Abstract: A cooling device for the casing of a jet engine, includes a cooling tube and a supporting device, the supporting device including an attachment plate and an attachment clamp, the attachment clamp including a clamp body surrounding the cooling tube and an attachment element attached to the attachment plate, wherein the attachment plate includes: an opening; and an attachment tab secured to the main wall of the attachment plate and arranged on at one portion of the periphery of the opening, the attachment clamp passing through the opening, and the attachment element of the attachment clamp being attached to the attachment tab.

Abstract: The main purpose of the invention is an interface device (1) between first (2) and second (3) turbomachine elements, characterised in that it comprises an annular air inlet structure (4) comprising opposite first (5) and second (6) parts, designed to come into contact with first (2) and second (3) turbomachine elements respectively, the first part (5) being configured to be in swivel contact with the first element (2), and an elastic return device (7) that can be placed around the air inlet structure (4) and designed to come into contact with at least the first turbomachine element (2).

Abstract: The present invention relates to a two-spool gas turbine engine including an HP turbine stator ring and an exterior wall of the transition channel between the HP and LP stages, a first enclosure for controlling the stator ring, and a second enclosure for distributing air for blowing the exterior wall of the transition channel. The engine is characterized in that the two enclosures are placed in communication via an orifice controlled by a valve adapted to be open when the pressure P1 in the first enclosure is greater than the pressure P2 in the second enclosure, and closed when P1<P2.

Abstract: The exhaust casing of a turbomachine includes a cylindrical jacket for guiding a flow of exhaust gas and for defining a hub cavity inside the casing, the jacket including at its ends an annular flange and a radial annular portion extending inwards and formed with an annular rim that is designed to be received in an annular groove of the inner wall of the exhaust casing to close the hub cavity in substantially sealed manner.

Abstract: A sectorized nozzle for a turbomachine, the nozzle being made up of cylindrical sectors and comprising two annular platforms interconnected by substantially radial vanes, together with an annular rail for supporting elements of abradable material, each inner platform having longitudinally-extending edges that are V-shaped, and each rail sector having, on at least one of its sides, means for bearing axially on corresponding means provided on an adjacent nozzle sector.

Abstract: A turbine stage in a turbomachine is disclosed. The stage includes a wheel mounted in a ring carried by a turbine casing, and a nozzle situated upstream from the wheel and including an annular fastener rim for fastening to the turbine casing, sealing being provided between the outer rim of the nozzle and the upstream end of the ring by a radial annular sheet bearing axially at its inner and outer peripheries against a downstream face of the outer rim of the nozzle, with its middle annular portion being axially spaced apart from the outer rim of the nozzle and bearing axially against the upstream end of the ring.

Abstract: The present invention relates to a two-spool gas turbine engine including an HP turbine stator ring and an exterior wall of the transition channel between the HP and LP stages, a first enclosure for controlling the stator ring, and a second enclosure for distributing air for blowing the exterior wall of the transition channel. The engine is characterized in that the two enclosures are placed in communication via an orifice controlled by a valve adapted to be open when the pressure P1 in the first enclosure is greater than the pressure P2 in the second enclosure, and closed when P1<P2.

Abstract: The exhaust casing of a turbomachine includes a cylindrical jacket for guiding a flow of exhaust gas and for defining a hub cavity inside the casing, the jacket including at its ends an annular flange and a radial annular portion extending inwards and formed with an annular rim that is designed to be received in an annular groove of the inner wall of the exhaust casing to close the hub cavity in substantially sealed manner.

Abstract: A sectorized nozzle for a turbomachine, the nozzle being made up of cylindrical sectors and comprising two annular platforms interconnected by substantially radial vanes, together with an annular rail for supporting elements of abradable material, each inner platform having longitudinally-extending edges that are V-shaped, and each rail sector having, on at least one of its sides, means for bearing axially on corresponding means provided on an adjacent nozzle sector.

Abstract: A turbine stage in a turbomachine, the stage comprising a wheel mounted in a ring carried by a turbine casing, and a nozzle situated upstream from the wheel and including an annular fastener rim for fastening to the turbine casing, sealing being provided between the outer rim of the nozzle and the upstream end of the ring by a radial annular sheet bearing axially at its inner and outer peripheries against a downstream face of the outer rim of the nozzle, with its middle annular portion being axially spaced apart from the outer rim of the nozzle and bearing axially against the upstream end of the ring.