Safran Helicopter Engines

Yvan Ludovic Lameignere

Loïs Pierre Denis Vive

Hubert Pascal Verdier

Nicolas Roland Guy Savary

Jean-Luc Breining

Olivier Lamaison

Denis Daniel Jean Boisseleau

Thomas Gabriel Elie Gatteau

Chritophe Nicolas Henri Viguier

Claude Marie Michel Berat

Albert Josse

A rotor wheel for an aircraft turbine engine has a disc with a main axis and cells at its outer periphery. The cells extend along the axis, and each has a bottom and two side flanks. Vanes are mounted in the cells of the disc, each vane including a blade connected by a platform to a root mounted in one of the cells. Each root includes, at its radially inner end, a lobe with a first axial end having a circumferential notch and a second axial end having a radially inward facing stop configured to axially bear on a first face of the disc. An annular ring engages the notches of the vanes and is axially clamped against a second face of the disc. Each lobe has a radially inward facing projecting bulb configured to radially bear on the surface of the bottom of the corresponding cell.

Rotor wheel for an aircraft turbine engine

A component () for supporting at least one bearing () for a turbine engine () comprising: two coaxial walls, internal () and external () walls respectively, defining a gas flow vein () between them and interconnected by a row of arms (); an external ferrule () comprising an internal peripheral edge () connected to the external wall () and an external peripheral edge () connected to an external mounting flange (); an internal ferrule () comprising an external peripheral edge () connected to the internal wall () and an internal peripheral edge () comprising an internal mounting flange (); at least one of the ferrules (), which at the peripheral edge () thereof is connected to the corresponding wall (), having a general shape which is corrugated about an axis (X-X) of the component ().

Annular component for supporting a turbine engine bearing

The invention relates to a pre-vaporizing pipe () for a combustion chamber of a turbomachine, comprising a generally elongate main body (), comprising a first end portion () delimiting an inlet duct () in which a fuel injector is to be mounted, the body () having an external surface () having a first length (L) that extends from the portion () to at least one first fuel outlet end piece (), and a second length (L) that extends the first length (L) from the end piece () and that extends from the end piece () to a second fuel outlet end piece (). According to the invention, inside the body () there is a first channel () connecting the duct () to the end piece () and a second channel () which is distinct from the first channel () and which connects the duct () to the end piece ().

Pre-vaporizing pipe, combustion assembly provided therewith and turbomachine provided therewith

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Moissy-Cramayel, France

Yvan Ludovic Lameignere