Safran Aircraft Engines

Pauline Anne Freche

Laurent Jablonski

Kamel Benderradji

Delphine Hermance Maxime Parent

Florent Combier

Jean-Claude Belouar

Joel Robert Mathieu

Eric Jean-Paul Guinoiseau

Cedric Louis Joseph Laurent

Cédric Louis Joseph Laurent

A turbine engine assembly including a first rotor element and a second rotor element extending around a longitudinal axis X and coupled to one another by a gear coupling, the first rotor element including teeth and the second rotor element including complementary teeth which extend along the longitudinal axis and form the gear coupling. The first and second rotor elements each include a first and a second radial flange which are annular and arranged facing one another, and the assembly includes a sealing device configured to ensure that the gear coupling is sealed at the first and second flanges.

Turbine engine rotor element assembly equipped with a sealing device

The invention relates to a diffuser () of a radial or hybrid compressor () comprising an internal shroud (), an external shroud () and a series of vanes (), the trailing edge () of each vane () being curved in such a way that a distance (di) between the leading edge () and the trailing edge () of the vane () at the mid-height point (h/) of the vane () is 5% to 15% shorter than a distance (d) between the leading edge () and the trailing edge () of the vane () at the level of the internal shroud (), the trailing edge () also having an evolving cross section comprising a first part forming a low wall () in the vicinity of the external shroud () and having a height (H) equal to at most 10% of the height (h) of the vane (), a curved second part and a third part forming a low wall () substantially identical to the first part.

Reinforced axial diffuser

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Moissy-Cramayel, France

Pauline Anne Freche