Safran Aircraft Engines

Snecma

Francois Jean Comin

Romain Nicolas Lagarde

Laurent Jablonski

Philippe Gérard Edmond Joly

Jean-Marc Claude Perrollaz

Charles Jean-Pierre Douguet

Serge Rene Morreale

Damien Merlot

Arnaud Jean-Marie Pierrot

Pierre-Guillaume Bardin

Marie-Oceane Parent

Sylvain Van Ceulen

Julien Meyer

Claude Marcel Robert Majeux

Romain Lagarde

Philippe Gerard Joly

Claude Marcel Majeux

A turbomachine assembly is provided. The assembly includes: a first rotor module including a first blade, a second rotor module, connected to the first rotor module, and including a second blade of smaller length than the first blade, and a damping device including a plurality of first radial external surfaces supported with friction against the first module. The damping device is stepped, and includes a second radial external surface supported with friction against the second module, so as to couple the modules for the purpose of damping their respective vibrational movements during operation.

Damping device

An assembly for a turbomachine including a first rotor module () with a first blade (), and a second rotor module (), connected to the first rotor module (). The second rotor module includes a second blade with a smaller length than the first blade (). A damping device () is attached to the second rotor module () and includes a radial external surface () supported with friction against the first module (), so as to couple the modules () for the purpose of damping their respective vibrational movements during operation.

The invention relates to a turbomachine assembly () comprising:

An assembly forming a gasket for a turbomachine, includes a brush seal made of a plurality of sealing elastic bristles surrounding a core, a retaining ring including a recess to at least partly accommodate the brush seal, and a bearing cover, placed in contact with the brush seal to hold it in position against the retaining ring, the brush seal being located between the retaining ring and the bearing cover.

Assembly forming a gasket for a turbomachine, comprising a brush seal

A system for attaching electrical equipment to a metallic support and including a pin designed to be inserted through a through-housing of the metallic support and a metallic insert of the electrical equipment, and a device for insulating the metallic support, extending between the metallic support and the metallic insert. The system also includes a mechanical retention device designed to apply load to the insulating device so as to keep them in contact with the metallic support and with the metallic insert.

System for attaching electrical equipment to a metallic support

The invention relates to an assembly for a turbine engine, the assembly comprising a tubular shaft (), a nut () screwed onto an end portion of said tubular shaft (), and a locking member () for locking the nut () on the shaft (), said member () including means () for coupling in rotation with the nut () and means () for coupling in rotation with the shaft (), said member () being movable between a position for coupling the nut () in rotation relative to the shaft (), and a position for releasing the nut () relative to the shaft (). The nut () includes a housing () in which said member () is suitable for being held when in its release position.

Assembly for a turbine engine

A relief valve in a turbomachine is disclosed. The valve includes a gate designed to be mounted so as to pivot about a shaft for the opening and closing of an orifice for the passage of air, a seal, and an attachment device for attaching the seal to the peripheral edge of the gate. The gate and the attachment device are made of a plastic and formed of a single piece or secured to one another by welding or bonding.

Growing community of inventors

Melun, France

Francois Jean Comin