Safran Aircraft Engines

Safran

Pierre Jean Faivre D'arcier

Thomas Alain De Gaillard

Guillaume Pascal Jean-Charles Gondre

François Charleux

Jérémy Guivarc'h

Clément Pierre Postec

Mattéo Minervino

Damien Bruno Lamouche

Tony Alain Roger Joël Lhommeau

Jérémy Philippe Pierre Edynak

Jeremy Guivarc'h

Thibaut Dominique Augustin Girard

Lola Auliac

Jeremy Philippe Pierre Edynak

Vincent Lionel René Maison

A propeller blade or airfoil for a turboprop engine made from composite material including a matrix-densified fibrous reinforcement, the propeller blade or airfoil including, in the direction of its span, a root and an aerodynamic profile. The fibrous reinforcement includes a fibrous preform having three-dimensional weaving with a root preform portion and an aerodynamic profile preform portion. The fibrous preform includes a separation delimiting a recess that forms a cavity extending both into the root and into the aerodynamic profile. A spar is present in the cavity, the spar including an aerodynamic profile shaping portion positioned in a first portion of the cavity and a root shaping portion positioned in a second portion of the cavity. The root has a rotationally symmetric shape.

Propeller blade or vane having a hollow composite root

A turboprop engine blade or propeller airfoil made of composite material includes a fiber reinforcement densified by a matrix, the blade or propeller airfoil including along a longitudinal direction a root and an aerodynamic profile. The fiber reinforcement includes a fiber preform having a three-dimensional weave with a root preform part located in the root and an aerodynamic profile part located in the aerodynamic profile, the root preform and aerodynamic profile parts being connected to one another by three-dimensional weaving. The root preform part includes two woven skins wound around an insertion element.

Propeller blade or airfoil with wound composite root

The invention relates to a fan rotor for a turbomachine, including a fan disk, fan blades with a leading edge and a trailing edge, platforms inserted between the blades and fixed to the periphery of the disk, each including an aerodynamic surface extending from the leading edges to the trailing edges of the blades. The aerodynamic surface includes an upstream longitudinal portion on the side of the leading edges and a downstream longitudinal portion on the side of the trailing edges, the upstream longitudinal portion being supported by a first member of the platform fixed to the disk in a pivotable manner, and the downstream longitudinal portion being independent of the upstream longitudinal portion and supported by a second member of the platform which is independent of the first member and fixed to the disk in a pivotable manner.

Turbomachine fan rotor

Blower vane for an aircraft turbine engine, the vane comprising a blade connected to a root, the vane being made of a woven fibre-based composite material embedded in a polymeric resin, the vane further comprising a medium for identifying the vane, which is a radio-identification medium, the blower vane being characterised in that it comprises at least a first portion the fibres of which are only electrically conductive fibres, and at least a second portion the fibres of which are formed by a mixture of electrically conductive fibres and non-electrically conductive fibres, and in that the identification medium is located in or on the second portion.

Composite vane for an aircraft turbine engine

The present invention relates to a turbomachine rotary-fan blade (), comprising a body () made of a composite material, a metal reinforcement part () comprising a metal upstream nose (), characterised in that the metal upstream nose () comprises, at least on the metal part () of the blade tip, a recess () of longitudinally tapering thickness (AX), delimiting on the metal part () over a height (H) at least one metal projection () with prescribed wear, which has a longitudinally tapering thickness and which is configured to detach at least partially in the presence of tangential friction in the second thickness direction (EP) against the metal part (), the recess () and the metal projection () with prescribed wear extending the first metal fin () and/or the second metal fin () and/or the upstream edge () of the body () made of composite material.

Turbomachine rotary-fan blade, fan and turbomachine provided therewith

The invention relates to a turbomachine rotary-fan blade having a predetermined breaking zone, which extends from the upstream edge along a given length and from the blade-tip edge over a given height. According to the invention, the body is made of a composite material comprising a fibre reinforcement obtained by three-dimensional weaving of warp and weft strands, and a resin matrix in which the fibre reinforcement is embedded, and has, in or in the vicinity of the zone, a discontinuity of at least some of the strands, configured such that the zone partially detaches when there is tangential friction in the thickness direction against the blade-tip edge, the height being less than 3% of the aerodynamic stream height of the blade.

Growing community of inventors

Moissy-Cramayel, France

Pierre Jean Faivre D'arcier