Safran Aircraft Engines

Snecma

Bertrand Pellaton

Stephane Pierre Guillaume Blanchard

Benoit Guillaume Silet

Josselin Luc Florent Sicard

Josselin Sicard

Youki Olivier Ito-Lardeau

Anne-Flore Karine Houlet

Helene Barret

Hélène Marie Barret

Baptiste Jouy

Josselin Luc Sicard

Helene Marie Barret

A turbine rotor for a gas turbine engine, includes an upstream turbine disk; a downstream turbine disk; an annular flange; a first ferrule connecting the upstream turbine disk to the annular flange; a second ferrule connecting the downstream turbine disk to the annular flange; an air flow separator device including: a first part, forming a first ring, arranged between the upstream turbine disk and the downstream turbine disk; a second part, forming a second ring, having a first portion facing the downstream turbine disk, and a second portion arranged between the first ferrule and the second ferrule; and a thermal insulation area arranged between the first part and the second part.

Turbine rotor for a gas turbine engine

An impeller for a turbine engine is disclosed, such as a turbojet engine or a turboprop engine of an aircraft, for rotating about an axis of rotation in a predetermined direction of rotation and for having a flow of gas passing therethrough, comprising a series of blades distributed circumferentially about the axis of rotation of the wheel, the radially external end of each blade comprising a heel supporting at least one radially external lip, extending circumferentially in an oblique direction relative to the radial plane perpendicular to the axis of rotation, the lip being angled circumferentially in the downstream direction in the aforementioned direction of rotation such as to enable a compression of the gases located upstream from the lip during the rotation of the impeller.

Turbine engine impeller

A turbine wheel including a plurality of blades having roots engaged axially and held radially in slots in a disk alternating between teeth of the disk, in which the blades have platforms arranged circumferentially end to end and each connected to a blade root by a tang, is provided. Separator walls extend from the tangs in a circumferential direction and from upstream to downstream so as to define radially between the platforms and the teeth of the disk at least a radially inner cavity and a radially outer cavity between two adjacent tangs.

Turbine wheel in a turbine engine

Growing community of inventors

Verneuil l'Etang, France

Bertrand Pellaton