Snecma

Francois Maurice Garcin

Jean-Pierre Lombard

Jean-Pierre Francois Lombard

Jerome Alain Dupeux

Stephane Jean Joseph Baumhauer

Stephane Jean Baumhauer

Nicolas Christian Triconnet

Mathieu Caucheteux

Laurent Gilles Dezouche

Pierrick Jean

Daniel Bernard Dao

Eric Seinturier

Olivier Abgrall

Etienne Balmes

Christian Paleczny

Eric Landragin

An impeller including a blade, a support of the blade which extends substantially radially, at least one intermediate part extending, in a substantially axial direction, between the blade and the support of the blade, and at least one damping device placed on at least one face of the intermediate part is disclosed. The damping device is segmented in an axial and/or circumferential direction into at least two elementary damping devices.

Movable impeller for a turbojet and turbojet comprising same

A lever for rotating about its pivot a turbomachine variable-pitch stator vane: including a first zone for attachment to a lever drive member, a second zone for attachment to the variable-pitch stator vane, and a third zone of elongate shape between the first zone and the second zone is disclosed. A vibration-damping laminate is applied to at least one surface portion of at least one of the zones of the lever. The laminate includes at least one layer of viscoelastic material in contact with the surface portion and a backing layer of rigid material.

Lever for rotating a turbomachine variable-pitch stator vane about its pivot

A cylindrical casing for a turbomachine that is suitable for receiving a rotor fitted with at least one bladed wheel is disclosed. The casing includes a device for preventing instability during contact between the casing and the bladed wheel. The device includes a succession of elements disposed around the circumference of the casing, and presenting different stiffnesses between two adjacent elements. The number of elements having the same stiffness not being equal to a multiple of the wave number of the vibratory mode of the bladed wheel that is to be inhibited. The invention is applicable to a compressor, a turbine, or a fan.

Turbomachine casing including a device for preventing instability during contact between the casing and the rotor

A turbomachine stator forming a stator vane ring or upstream guide vane element including a plurality of vanes placed radially between a first inner ring and a second outer ring is disclosed. The two rings are concentric and the second ring has a cylindrical outer surface portion. The stator is characterized in that, on the outer surface portion, at least one vibration-damping laminate is attached. The laminate includes at least one layer of viscoelastic material in contact with the surface portion and one counterlayer of rigid material.

Damping device for turbomachine stator

The invention relates to a turbomachine thermomechanical part forming a body of revolution about a longitudinal axis, and including at least one abradable ring for a labyrinth seal. In characteristic manner, the abradable ring is made up of angular sectors that present different stiffnesses between adjacent pairs of sectors. The invention is applicable to a compressor, a turbine, or to a rotor and stator assembly.

Thermomechanical part constituting a body of revolution about a longitudinal axis and including at least one abradable ring for a sealing labyrinth

A hollow shaft of a turbomachine including a cylindrical wall with an inner surface portion and at one end a member for attachment to a rotor disk of the turbomachine is disclosed. The shaft also includes a damping device wherein at least one vibration-damping laminate is attached to the inner surface portion. The laminate includes at least one layer of viscoelastic material in contact with the surface portion and a counterlayer of rigid material.

Damping device for a shaft of a turbomachine

A sector of a compressor guide vanes assembly or a sector of a turbomachine nozzle assembly. It comprises an inner ring sector (), an outer ring sector () and a multitude of blades () connecting the inner ring sector () to the outer ring sector (). The outer ring sector () or the inner ring sector () comprises radial cuts () situated between two consecutive blades () in such a way as to split them into the same number of elementary sectors as there are blades. Housings () are provided, secant to the radial cuts (), damping inserts () being positioned in said housings.

Sector of a compressor guide vanes assembly or a sector of a turbomachine nozzle assembly

A device for fastening two parts to each other includes fastening screws extending in aligned passages in the two parts and receiving nuts, and a removable element for preventing the screw heads from moving during tightening or loosening of the nuts on the screws, this removable element cooperating with one of the two parts for preventing rotation of the screw heads relative to this part.

Growing community of inventors

Paris, France

Francois Maurice Garcin