Snecma

Gregory Nicolas Gerald Gillant

Olivier Belmonte

Sylvain Dousseaud

Stéphane Clemot

A part to modify the profile of an aerodynamic jet, including: a first face configured to be secured on the aerodynamic jet, and a second face defining a modified aerodynamic jet profile, configured to modify an initial profile of the aerodynamic jet.

Part to modify the profile of an aerodynamic jet

The invention relates to an insert for a turbine engine test vane including the insert and a vane body. The insert includes at least two external surfaces. The insert is configured to fit into the vane body, such that the external surfaces are vane aerodynamic surfaces each forming part of a vane aerodynamic profile.

Insert with an external surface which is part of at least one aerodynamic profile of a turbomachine test blade

A retaining ring assembly for at least one blade of a rotor disk of a turbine engine and a supporting flange for the ring. The flange and the ring are rotating parts having an axis X, the flange including an attachment edge configured to be connected to the rotor disk and a free edge configured to bear against the retaining ring; and the flange bears against the ring such that the bearing force of the flange on the ring has an axial component and a radial component relative to the axis of revolution X.

Retaining ring assembly and supporting flange for said ring

A radial annular flange of a rotor or stator element of a turbomachine including, at an inner/outer periphery, alternating solid portions and hollow portions, the solid portions including orifices for passing fastener bolts. The flange in the bottom of at least one hollow portion has a radius relative to the axis of the turbomachine that is less/greater than the radius of a circle that is tangential to the outsides/insides of the orifices for passing bolts through the solid portions.

Annular flange for fastening a rotor or stator element

A low-pressure turbine for a turbomachine including turbine disks with festooned annular flanges for fastening to a festooned annular flange of a drive cone connecting the turbine disks to a turbine shaft, solid portions of the festooned annular flanges of the turbine disks and of the drive cone being connected to peripheries of the turbine disks and of the drive cone, respectively, via concave filets that are asymmetrical.

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Mennecy, France

Gregory Nicolas Gerald Gillant