Safran Aircraft Engines

Maxime Paul Numa Givert

Alexandre Gimel

Julien Fabien Patrick Becoulet

Ba-Phuc Tang

Alexandre Jean-Marie Tan-Kim

Marc Soisson

Denis Gabriel Trahot

Elsa Maxime

Josserand Jacques André Bassery

Gabriela Mihaila

Christophe Damour

Disclosed is an assembly for a turbomachine that includes connection elements having respective radial flexibilities, wherein a ratio of a first of the respective radial flexibilities to a third of the respective radial flexibilities is strictly lower than 10% and/or a ratio of the first of the respective radial flexibilities to a second of the respective radial flexibilities is strictly lower than 4%.

Flexibilities in a gas turbine engine with speed reducer

A turbine engine has a blade with lower and upper surfaces. The blade has a root at a radially external end and includes a transverse head section in a plane perpendicular to a radial direction of the blade, taken at the radially external end with a first center of gravity. The root has a second center of gravity defined in a plane parallel to the transverse head section and transversely offset from the first center of gravity. The second center of gravity is defined in a predetermined zone at least partly demarcated by a V that is open towards the lower surface and includes a peak, the orthogonal projection of which on the transverse head section is located on the first center of gravity.

Vane for a turbine engine with optimized heel and method for optimizing a vane profile

A rough cast blading of this blade includes, a suction sidewall and/or a pressure sidewall of this blading intended to respectively form the suction sidewall and/or the pressure sidewall of the blade, a casting allowance extending over a determined width from a trailing edge of the blading intended to form the trailing edge of the blade in the direction of a leading edge of the blading intended to form the leading edge of the blade, except for a reserved area adjacent to the trailing edge of the blading and whose width is at least one radius of the trailing edge of the blading, over at least part of the height of the blading.

Rough cast blading with modified trailing edge geometry

Growing community of inventors

Moissy-Cramayel, France

Maxime Paul Numa Givert