Snecma

Safran Aircraft Engines

Thomas Langevin

Maurice Guy Judet

Fabrice Garin

Michel Gilbert Roland Brault

Stephane Pierre Guillaume Blanchard

Olivier Belmonte

Sebastien Jean Laurent Prestel

Guillaume Sevi

Renaud James Martet

Damien Bonneau

Adrien Paixao

Benoit Guillaume Silet

Patrick Claude Pasquis

Cyril Verbrugge

Michel Gilbert Brault

François Sfarti

Stevan Le Goff

Jean Charles Marie Coussirou

Jean-Pierre André Joseph Mourlan

Bruno Druez

Hélène Quillent

Jean-Pierre Andre Mourlan

Francois Sfarti

Helene Quillent

Stefan Legoff

A blade and a sealing element forming an assembly for a turbomachine turbine. The blade includes an airfoil and a platform to which the sealing element is connected. An internal channel passes through the platform so as to draw off fluid circulating in a primary duct that it delimits and to inject the thus drawn-off fluid into an inter-lip cavity delimited by the sealing element.

Turbine blade for an aircraft turbomachine, provided with a channel for ejecting a primary flow towards an inter-lip cavity

A turbine blade for a turbomachine includes a turbine blade with a leading edge and a trailing edge. The blade includes a radially outer platform with at least one lip extending radially towards the outside. The radially outer end of the leading edge and/or of the trailing edge of the turbine blade airfoil extending axially upstream and/or downstream, respectively, in relation to the platform. The blade has at least one partition extending radially towards the outside from the radially outer end of the turbine blade airfoil and axially between the leading edge and the upstream end of the platform and/or between the trailing edge and the downstream end of the platform.

Turbine blade

A gas turbine casing made of organic matrix composite material includes reinforcement densified by an organic matrix defines an inside volume. On its inside face the casing has a structural part with a first face facing the inside face of the casing, and an opposite second face defining a flow passage portion. Recesses opening out into the inside volume of the casing are present between the inside face of the casing and the first face of the structural part facing the inside face of the casing. In the event of a fire, the recesses allow gas coming from degradation of the resin of the casing to be discharged into the flow passage.

Casing made of organic matrix composite material that facilitates the discharge of smoke

An assembly with a turbine disk for a gas turbine engine and a bearing-supporting journal, the turbine disk having a radial annular fastening flange secured to a radial annular part of the journal by bolts, the bolts passing successively through fastening bores formed in the radial annular fastening flange of the turbine disk and in the radial annular part of the journal, the radial annular part of the journal having air circulation openings, the openings being formed between the fastening bores of the journal.

Assembly including a turbine disk for a gas turbine engine and a bearing-supporting journal, and cooling circuit for the turbine disk of such an assembly

A radial annular flange including in inner or outer periphery alternating solid portions including orifices for passing fastener bolts, and hollow portions having bottoms that are substantially flat. The bottom of at least one keying hollow portion is situated radially inside, or outside, respectively, a circle centered on the axis of the flange and externally, or respectively internally, tangential to the orifices. Two hollow portions are situated on either side of the keying hollow portion having bottoms of concave curved shapes situated radially on the outside, or respectively on the inside, relative to the flat bottoms of the other hollow portions.

Annular flange for fastening a rotor or stator element in a turbomachine

A turbine shroud ring sector for a turbomachine supported at the upstream end by a downstream support of a turbine casing with circular sliding including a first stop able to collaborate with a second stop borne by an element of the turbomachine adjacent to the shroud ring in order to immobilize the shroud ring circularly is disclosed. The sector includes, on an end facing the element, a recess able to allow the second stop to pass to come into contact with the first stop. The recess is cut substantially in the form of a rectangle having, at the bottom of the recess, corners that are rounded in a circular arc of radius r. The bottom of the recess has a convex shape tangential to the circular arcs of the rounded corners and with a curvature that evolves between a radius of curvature r where it meets the rounded corners and a radius of R, greater than the radius r, at a point situated between the two rounded corners.

Turbine shroud ring with rotation proofing recess

The present invention relates to a turbomachine rotor balancing system comprising a balancing flange () provided with through-passageways (), the system further comprising balance weights () each mounted fixedly on the flange () by means of a first and a second screw/nut assembly () having a first and a second screw () passing through a first and a second passageway (). According to the invention, said first screw is pressing against a first tangential end side () of the first through-passageway, and at a distance from a second tangential end side, and the second screw is pressing against a second tangential end side () of the second through-passageway, and at a distance from the first tangential end side.

Balancing system for turbomachine rotor

A turbomachine rotor balancing system including a balancing flange provided with through-passageways, and balance weights mounted fixedly on the balancing flange by at least one screw/nut assembly passing through one of the passageways is disclosed. For each of the passageways, the flange has on its first face a first recess passing via the radial summit of the passageway. This first recess being deprived of contact with the screw head pressing on this first face. The flange has on its second face a second recess passing via the radial summit. The second recess being deprived of contact with the balance weight pressing on this second face.

A retention device for axially retaining a rotor disk flange, the device including a split annular retaining ring. The ring has an external face bearing against an internal face of the rim, thereby resulting in a first axial force, an internal face bearing against an external face of the root, thereby resulting in a second axial force, the axial forces being radially offset relative to each other, and an outer face bearing against an inner face of the base of the flange, thereby resulting in a radial force. The outer face of the ring presents an annular setback in such a manner that the radial force is situated in a plane that is offset axially relative to a radial plane passing through the center of gravity of the ring so as to obtain mechanical equilibrium between the forces acting on the ring.

Retaining device for axially retaining a rotor disk flange in a turbomachine

A device for balancing a turbomachine rotor includes at least one counterweight fitted to the rotor, wherein the counterweight includes two radial bearing surfaces oriented in two opposite radial directions, the said surfaces interacting with two radial bearing surfaces made on the rotor, the counterweight being held against the rotor by an axial retention device. In particular, the axial retention device can be a bolt with a nut, the bolt holding the counterweight against a coupling flange fixed ly attached to the rotor, including an axial bearing surface and the radial bearing surfaces.

Balancing device of a turbomachine engine

A turbine module for a gas turbine engine includes at least one turbine disk and a disk-shaped component mounted on the turbine disk upstream relative to the gas flow. The module can be assembled to the compressor of the engine, wherein the component is preassembled to the turbine disk, before the module is assembled to the compressor, by bolting to an attachment flange fixedly attached to the turbine disk.

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Dammarie les Lys, France

Thomas Langevin