Abstract: Turbine stage in a turbine engine, including a wheel with blades rotating inside a sealing ring (22) held by a casing (24) of the turbine, and an annular thermal protection sheet mounted between the casing (24) and the ring (22), wherein the annular thermal protection sheet is formed by a plurality of curved plates (54, 56) mounted end-to-end and attached by pins (70) to the casing (24).

Abstract: A variable-section turbomachine nozzle comprises a plurality of moving flaps, and a moving flap control system comprising control levers each associated with a respective moving flap, the control levers comprising both controlled levers that are actuated directly by actuators, and follower levers that are actuated by the controlled levers via transmission links. When the nozzle is at rest, the flaps associated with the follower levers present a radial offset relative to the flaps associated with the controlled levers.

Abstract: This invention relates to a turbine stator (5) for an aircraft turbine engine, comprising: a stator wall (46) supporting a high pressure air injector (50) fixed on the downstream side; an annular abradable element support (54) the lower radial end (54a) of which is fixed to said high pressure air injector and its upper radial end (54b) is fixed to said stator wall, such that they jointly delimit a cavity (58) under pressure. According to the invention, it also comprises at least one vibration damping device (74) located in said cavity (58) under pressure, said vibration damping device being in contact with each of the two elements taken among said stator wall (46) and said annular support (54).

Abstract: High-pressure turbine of a turbomachine A high-pressure turbine (10) of a turbomachine, comprising at least one upstream guide vane element (16) and an impeller (18) mounted so as to rotate inside ring sectors (20) attached to an annular support (24) which is suspended from an outer casing (22), the upstream guide vane element comprising, at its radially inner end, means of attachment to an inner casing and, at its radially outer end, means (102, 104) for pressing axially on a fixed element (90) of the turbine that is suspended from the outer casing independently of the annular support for attachment of the ring sectors.

Abstract: A turbine stage in a turbomachine comprising ring sectors (20) arranged about a turbine impeller (18), and an annular support (50) supporting the ring sectors and attached to a turbine casing (22), this annular support being able to be deformed elastically in the radial direction to cushion at least a portion of the deformations of the turbine casing in operation.

Abstract: Mounting an exhaust cone of composite material. The exhaust cone is mounted to extend an adapter ring and it is held in particular by elastic stress means that act axially.

Abstract: The jet engine of the invention comprises an exhaust nozzle of variable section, comprising at least one flap pivot mounted about a pin, the pin being joined to the fixed structure of the jet engine via two braces each comprising a bore for housing the pin, the flap being pivot commanded by an actuating cylinder, connected to two fasteners which each comprise a bore through which the pin passes and about which they rotate. The jet engine is characterized by the fact that the pin, the bores of the braces and bores of the fasteners are arranged so that the contacts between the pin with the bore walls of the braces and with the bore walls of the fasteners are made over convex surfaces. Therefore, when in operation, in the event of pin bending the contact surfaces follow this convex shape and are suitably distributed.

Abstract: A variable-section turbomachine nozzle comprises a plurality of moving flaps, and a moving flap control system comprising control levers each associated with a respective moving flap, the control levers comprising both controlled levers that are actuated directly by actuators, and follower levers that are actuated by the controlled levers via transmission links. When the nozzle is at rest, the flaps associated with the follower levers present a radial offset relative to the flaps associated with the controlled levers.

Abstract: A variable-section nozzle for a turbomachine, the nozzle comprising a plurality of moving flaps mounted on the downstream end of an annular casing of the turbomachine, a moving flap control system comprising control levers each associated with a respective moving flap and at least one actuator for actuating the control levers, and a plurality of pairs of arms each forming a control lever support, the arms of each support being secured both to the casing and to a control lever, each pair of arms forming a control lever support being formed as a single piece.