Safran Aircraft Engines

Joao Antonio Amorim

Nicolas Xavier Trappier

Stéphane Pierre Guillaume Blanchard

Patrick Jean Laurent Sultana

Matthieu Simon

Maxime Aurélien Rotenberg

Antoine Hervé Dos Santos

Maxime Aurelien Rotenberg

Pascal Grégory Casaliggi

Vahe Kupelian

Loic Ansart

Vahé Kupelian

The present invention relates to a turbine rotor () comprising a rotor disc (), provided at its periphery with a plurality of axial cells () for receiving a bilobed root () of a blade (), each cell () comprising a radially inner cavity () and a radially outer cavity (). This rotor is characterised in that it comprises a ring () for axially retaining the blade roots and an annular flange (), the ring () comprising a radially inner portion provided with notches () and being arranged against the upstream face () of the disc (), so that each of its notches () is located opposite a cell () of the disc (), the flange () being secured against the upstream face of the ring (), forming a space (E) with said disc (), and comprising at least one air-intake opening () which opens into said space (E), and in that each blade () comprises a groove () for receiving the outer circumferential edge () of said ring ().

Turbine rotor comprising a blade stop ring configured to aid the cooling of the blade roots

A guide vane assembly for a turbomachine extending about an axis and having at least one stator vane which extends from a platform, a first flange extending radially inwards from the platform, a sealing element being mounted on the first flange by way of a sliding means that allows the sealing element to move radially with respect to the first flange, the sliding means having at least one pin mounted on the sealing element and/or on the first flange and engaged in at least one oblong orifice extending radially and formed in the first flange and/or in the sealing element, wherein the pin and/or the orifice are covered, at least partially, by a cover plate situated axially opposite of at least a part of the pin.

Guide vane assembly for a turbomachine

A control valve composed of sectors of stationary blades, which are externally connected to a stator, includes an inner platform divided into an outer portion formed of sectors and associated, by radial slide connections, with an inner portion in the form of a ring which is continuous over a circumference, which carries an abradable seal. Springs ensure the radial position of the crown, and the concentricity thereof to the rest of the machine. The diameter of the crown is essentially determined by the temperature of the gases which pass in front of it. The independence of the radial thermal deformations is ensured by slides composed of sliding sleeves.

Turbine engine stator control valve comprising a continuous and free sealing ring

An assembly for a turbine engine turbine includes a turbine rotor disc centered on a longitudinal axis and a turbine shaft centered on the longitudinal axis and driven in rotation by the rotor disc. Torque from the rotor disc is transmitted to the shaft, wherein the rotor disc is locked in translation relative to the shaft in the direction of the longitudinal axis by a screwed member on the shaft. Torque from the rotor disc is transmitted from the rotor disc to the screwed member when the torque ceases being transmitted from the rotor disc to the shaft. The screwed member has an unscrewing direction identical to the direction of rotation of the rotor disc in operation.

Turbine overspeed disengagement device for a turbine engine

Assembly including a rotor disc, an adjacent stator and a plurality of sealing elements secured to the rotor disc, the stator including an inner platform and a root bearing at least one abradable element configured to cooperate with the sealing elements, the sealing elements being placed in an enclosure formed by the abradable element, the enclosure being open to the inside and delimited axially by an upstream abradable edge and a downstream abradable edge, the enclosure being delimited radially by an outer abradable edge, at least one of the sealing elements including a first lip configured to cooperate with the upstream abradable edge or the downstream abradable edge, and a second, separate lip configured to cooperate with the outer abradable edge.

Sealing between a rotor disc and a stator of a turbomachine

A turbine rotor is fitted to a turbomachine and includes disks each containing a coupling portion with recesses each holding a root of a blade, and coupled to one another by a first annular ferrule attached to one of them close to the recesses, and second rotationally coupled ferrules, which are respectively coupled radially to the disks, which each consists of at least two semi-annular sectors, and which form with the associated disk a space which communicates with the recesses of the coupling portion of this latter disk. In addition, each first ferrule includes through-holes enabling air to enter this space, and then the recesses, intended to cool the coupling portion which couples its disk and the blade roots.

Growing community of inventors

Villeparisis, France

Joao Antonio Amorim