Safran Aircraft Engines

Patrick Jean Laurent Sultana

Olivier Renon

Matthieu Simon

Sebastien Jean Laurent Prestel

Stéphane Pierre Guillaume Blanchard

Renaud James Martet

Arnaud Lasantha Genilier

Julian Nicolas Girardeau

Sébastien Jean Laurent Prestel

Laurent Cédric Zamai

Clément Charles Jérémy Coiffier

Gaël Frédéric Claude Cyrille Evain

Olivier Arnaud Fabien Lambert

Joao Antonio Amorim

Vianney Simon

Patrice Jean-Marc Rosset

Simon Jean-Marie Bernard Cousseau

Marc-Antoine Anatole Got

Jean-Claude Christian Taillant

Maxime Aurélien Rotenberg

Maxime Aurelien Rotenberg

Antoine Hervé Dos Santos

Kenny Beauboit

Mathieu Patrick Henri Delalandre

Loic Ansart

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

The present invention relates to a nozzle guide vane for a turbine, having an axis of revolution and comprising:

Turbine nozzle guide vane comprising an annular sealing element

The invention relates to an assembly for a turbine engine, comprising a radially inner shaft () and a radially outer shaft (), said shafts () being coaxial and extending along an axis (X), means () for coupling said inner and outer shafts () in rotation, means () for axially holding the inner shaft () relative to the outer shaft (), means for centring the inner shaft () relative to the outer shaft (), characterised in that the centring means comprise a shim () for radial centring and for axial positioning, this shim being frustoconical and interposed between a frustoconical centring surface () of the inner shaft () and a corresponding frustoconical centring surface () of the outer shaft ().

Assembly for a turbine engine

The present invention relates to a rotating assembly of a turbomachine, comprising: —a shaft configured to drive a propeller of the turbo machine around an axis and comprising a first flange radially extending from the shaft, the first flange being monolithic with the shaft; —a sleeve fitted onto the shaft and comprising a second flange radially extending from the sleeve, the sleeve being attached to the first flange of the shaft by means of the second flange; and —at least one component connected to the shaft by means of the sleeve so as to be rigidly connected to the shaft to move therewith, the component comprising at least one sealing element.

Sleeve mounted onto a low-pressure shaft in a turbomachine

A turbine stator assembly including a guide vane assembly and a sealing ring bearing an abradable element of a dynamic sealing ring. The assembly includes pins secured to the sealing ring and cooperating with respective oblong openings formed in the guide vane assembly so as to allow a radial movement of the ring with respect to the guide vane assembly in order to compensate for differential thermal expansions. A seal is arranged so as to compensate for circumferential spaces between ring sectors forming the guide vane assembly.

Turbine stator assembly with a radial degree of freedom between a guide vane assembly and a sealing ring

A counter-rotating turbine for a turbine engine comprising an inner rotor having an inner drum to which is attached a plurality of inner impellers rotatably supported by a first shaft, an outer rotor comprising an outer drum to which is fastened a plurality of outer impellers rotatably supported by a second shaft coaxial with the first shaft, the outer rotor comprising a downstream impeller having a plurality of downstream moving blades extending between an outer shroud and an inner shroud, one upstream end of the outer shroud being attached downstream of said outer drum, the inner shroud being attached to the second shaft, at least one of the inner shroud and of the outer shroud comprising at least one flexible transition part configured to allow elastic deformation of said shroud in the radial direction.

Ferrule for counter-rotating turbine impeller

A counter-rotating turbine of an aircraft turbomachine, includes a casing including an endoscopy port configured for an endoscopy plug of a non-destructive testing device to pass into the casing. The endoscopy plug includes a mechanism for acquiring and transmitting images. The non-destructive testing device includes a mechanism for receiving and displaying images connected to the mechanism for acquiring and transmitting images by a wireless connection. First and second rotors are configured to rotate in opposite rotation directions, the second rotor having an endoscopy port in which the endoscopy plug is removably attached.

Counter-rotating turbine of an aircraft turbomachine and method for the non-destructive testing of a counter-rotating turbine rotor

Counter-rotating turbine (C) of a turbomachine () extending about an axis (X) and comprising an inner rotor configured to rotate about the axis of rotation (X), and comprising an inner drum on which an inner movable blading () is fixed, an outer rotor configured to rotate about the axis of rotation (X) in a direction opposite to the inner rotor, and comprising an outer drum () on which an outer movable blading () is fixed, the outer movable blading () comprising at least one fixing rod () extending through an orifice () of the outer drum (), the outer movable blading () being fixed to the outer drum () via a clamping means () fixed to the fixing rod () from an outer face of the outer drum (), a set ring () being disposed around the fixing rod () in the orifice () of the outer drum ().

Device for attaching blades in a contra-rotating turbine

A rotor disc for a turbomachine, the disc extending circumferentially about an axis and including a plurality of cavities configured to receive blade roots, each cavity including a downstream radial wall configured to axially block the blade root in the cavity, each downstream radial wall including a channel of ventilation of the cavity, including an inlet orifice which opens into the cavity and an outlet orifice which opens onto a downstream surface of the disc. An assembly for a turbomachine including such a disc and an upstream retention ring and a turbomachine including such an assembly.

Rotor disc with axial retention of the blades, assembly of a disc and a ring, and turbomachine

A rotor for a contrarotating turbine comprising a drum and a blading mounted inside, the drum comprising a hook delimiting a housing having an outer wall and an inner wall, the blading comprising a blade and an outer platform provided with spoiler placed inside the housing, wherein the rotor comprises a foil comprising an elastic inner wing and an outer wing, the outer wing being arranged radially between the spoiler and the outer wall, the inner wing having a first support with the inner wall and a second support with the spoiler, the inner wing being arranged in the housing so as to exert a force on the spoiler so as to press the spoiler against the outer wall via the outer wing.

Rotor for a contrarotating turbine of a turbine engine

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.

Turbine engine casing

The invention relates to a turbomachine assembly comprising: &#x2014;a casing comprising: &#x2014;an internal hub (), &#x2014;an external ferrule () extending around and at a distance from the internal hub (), &#x2014;a hollow arm (), provided with a longitudinal cavity () and connecting the internal hub () and the external ferrule (), &#x2014;a tube () configured to extend in the interior of the longitudinal cavity () of the hollow arm () of the casing and comprising a central support () comprising two elastic blades () and configured to exert a pressure on the wall () of the longitudinal cavity () when the tube () is extended in the interior of the longitudinal cavity (); characterized in that the material(s) of the elastic blades () is (are) such that said elastic blades () have a stress curve between the minimum and maximum stress curves of table A.

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Moissy-Cramayel, France

Patrick Jean Laurent Sultana