Safran Aircraft Engines

Snecma

François Jean Comin

Laurent Jablonski

Philippe Gérard Edmond Joly

Jean-Marc Claude Perrollaz

Romain Nicolas Lagarde

Serge René Morreale

Charles Jean-Pierre Douguet

Edouard Antoine Dominique Marie De Jaeghere

Damien Merlot

Anthony Lafitte

Rémi Roland Robert Mercier

Jean Marc Claude Perrollaz

Claude Marcel Robert Majeux

A turbomachine assembly includes a casing, first and second rotors, and a damper. The first rotor includes a disk and blades and is movable in rotation relative to the casing. The second rotor is movable relative to the casing around a longitudinal axis. The damper damps a movement of the first rotor relative to the second rotor. The damper includes first to third parts. The first part bears on the first rotor in a first area extending over a first angular sector around the longitudinal axis and applies a first centrifugal force on the first rotor. The second part bears on the first rotor in a second area that is smaller than the first angular sector and extends over a second angular sector around the longitudinal axis. The third part bears on the second rotor and applies a second centrifugal force on the second rotor.

Assembly for turbomachine

The present invention relates to an assembly for a turbomachine, comprising: a first rotor; a second rotor, and a damper () configured to damp a displacement of the first rotor relative to the second rotor, the damper comprising: a first portion () bearing against the first rotor and having a first thickness, a second portion () bearing against the second rotor and having a second radial thickness, and a third portion () connecting the first portion () to the second portion () and having a third radial thickness, wherein the third radial thickness is greater than at least one of the first radial thickness and the second radial thickness.

Assembly for a turbomachine

The present invention relates to a turbomachine assembly, comprising: a casing (), a first rotor () which is movable in rotation with respect to the casing () about a longitudinal axis (X-X), and comprising: *a disk (), and *a plurality of blades () capable of flapping with respect to the disk () during a rotation of the first rotor () with respect to the casing (), a second rotor () which is movable in rotation with respect to the casing () about the longitudinal axis (X-X), and a damper () which is configured to damp a displacement of the first rotor () with respect to the second rotor () in a plane orthogonal to the longitudinal axis (X-X), the displacement being caused by a flapping of at least one blade () among the plurality of blades (), the damper () comprising: o a first bearing part (): *bearing against the first rotor (), and *being configured to apply a first centrifugal force (C) to the first rotor (), o a second bearing part (): *bearing against the second rotor (), and *being configured to apply a second centrifugal force (C) on the second rotor (), and o a linking part (): *connecting the first bearing part () to the second bearing part (), and being thinned relative to the first bearing part () and the second bearing part (), and o a flyweight () which is fixedly mounted on the damper ().

Turbomachine assembly having a damper

The invention relates to a bladed disk () of a fan, comprising: a hub () comprising an outer radial platform () designed so as to define an inner gas flow stream in the turbomachine, a plurality of blades () comprising a root () connected to the platform (), a leading edge () and a trailing edge (), a groove formed in the platform () around part of the root () of each blade () in an area adjacent to the leading edge () and/or the trailing edge (), and a joint () placed in the groove () in such a way that it extends in the extension of the radially outer face () of the platform () in order to ensure a continuity of the inner flow stream.

Bladed disk flexible in the lower part of the blades

The invention relates to an assembly () for a turbomachine comprising: characterized in that the damping device () is annular while extending circumferentially around the turbomachine longitudinal axis (X-X) and in that the damping device () comprises a first radial external surface () supported with friction against the first module () as well as a second radial external surface () supported with friction against the second module (), so as to couple the modules () in order to damp their respective vibrational movements during operation.

Damping device

The invention relates to a turbomachine assembly () comprising:

A fan blisk for a turbomachine, the blisk comprising a hub delimited by an upstream face and a downstream face in addition to an outer peripheral face and a revolving inner peripheral face delimiting an inner opening, the hub carrying blades each having a leading edge and a trailing edge, the hub and the blades forming a one-piece assembly. The upstream face and/or the downstream face is offset, being located along the axis of rotation (AX) between the leading edges and the trailing edges of the blades, the blisk (bladed disk) comprising a filling member mounted on the offset face, the filling member comprising an inner centring ferrule engaging in the inner face of the hub, a radial portion resting against the offset face and an outer ferrule extending the outer peripheral face of the hub.

Growing community of inventors

Moissy-Cramayel, France

François Jean Comin