Snecma

Safran Aircraft Engines

Adrien Philippe Fabre

Stephane Rousselin

Christophe Paul Jacquemard

Jean-Marc Claude Perrollaz

Jean-Pierre Lombard

Jonathan Evert Vlastuin

Paul Antoine Foresto

David Marsal

Pierrick Jean

Adrien Laurenceau

Sébastien Tajan

Nicolas Horn

Norbert Lartigue

A variable-pitch vane including a plurality of propeller blades (). Each blade has a variable pitch according to a blade rotational axis (A) and a root (). A plurality of rotor connecting shafts (), each shaft having a foot () and a head (). The root () of each blade is mounted on the head () of a rotor connecting shaft via a pivot () in such a way as to allow each blade () to rotate according to the blade rotational axis (A), in which each blade () has a blade pitch, such that the blade rotational axis (A) is inclined relative to a radial axis (A) passing through the foot () of the corresponding shaft.

Variable-pitch vane

The invention relates to a method for manufacturing a blade made of composite material extending in a main elongation direction, the composite material of said blade comprising a fiber reinforcement densified by a matrix, the method comprising the following steps:

Method for manufacturing a propeller blade

A part includes a structure and at least one shape memory alloy element that is prestressed and embedded at least in part within said structure. The shape memory alloy is suitable for dissipating the mechanical energy of said structure when it vibrates in a given frequency band.

Part comprising a structure and a shape memory alloy element

The invention relates to a device () for controlling the setting of the blades () of a rotor () of a propeller, including a radial shaft (), the rotation of which modifies the setting of the blade (), a main spring (), a first end () of which is connected to the rotor () and a second end () of which is connected to a part () having an axial movement which drives the rotation of the radial shaft, and has a movement, the travel of which is offset relative to the first end in a direction () that is orthogonal to the axial direction (), the main spring exerting a resilient force which aims to move the parts toward a position in which the cord of the profile of the blade is orthogonal to the plane of rotation of the propeller, in the absence of part control by means of a jack.

Device for controlling blade angle, and propeller

A control system includes a power actuator coaxial with the axis of rotation of the propeller, and a transmission device connecting the power actuator to pivots, of the blades to be controlled, arranged substantially radially with respect to the axis of rotation. The actuator is a rotary jack whose mobile part rotates about the axis of rotation and is connected to the transmission device by a mobile mechanical connection which transforms the rotation imparted by the mobile part of the jack about the axis of rotation into a rotation of the blades about the axes of the pivots which are perpendicular to the axis of rotation.

System for controlling the pitch of the propeller blades of a turbomachine, and a turbomachine with a propeller for an aircraft with such a system

The invention concerns a device () for controlling the pitch of the blades of a fan () rotor (), comprising a radial shaft () linked to the blade, a connection rod () of which the axial movement controls the rotation of the radial shaft (), characterized in that it comprises:&#x2014;a first part () that is mobile in rotation with the rotor () about the axis () of the fan (), and on which one end of each connection rod () is secured,&#x2014;a second part () linked to the first part (), and&#x2014;at least three cylinders () capable of moving said second part () in axial translation, and of varying the tilt of said second part, the translation and tilt of the second part () driving a corresponding translation and tilt of the first part (), such that, when the first part () rotates, each connection rod () is subject to axial displacement of which the amplitude is variable and is a function of the tilt of the first part (), making it possible to vary the pitch of the blade during the rotation of same. The invention also concerns a fan, and a method for controlling the pitch of blades.

Device and method for controlling the pitch of blades

A method of fabricating a turbomachine rotor disk is disclosed. In the method, a metal container is defined, made up of a plurality of parts that define between them at least one annular cavity, an insert made of composite material is positioned in the at least one cavity, the assembly is subjected to hot isostatic compacting, and a rotor disk is machined.

Method of fabricating a turbomachine rotor disk

A process for manufacturing an integrally bladed disk for a turbomachine rotor by friction welding is disclosed. The manufacturing process includes arranging a plurality of blades in the form of a ring in a mold having symmetry of revolution; casting a degradable material, preheated to a temperature above its melting point, onto the ring of blades in the mold; extracting the molded ring which is obtained after the degradable material has solidified; welding the molded ring onto a disk; and eliminating the degradable material.

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Moissy Cramayel, France

Adrien Philippe Fabre