Safran Aircraft Engines

Lilian Yann Dumas

Alain Marc Lucien Bromann

Kamel Benderradji

Romain Nicolas Lagarde

Suzanne Madeleine Coustillas

Blaise Bergon

Pamela Dominique Daniele Reichert

Laurent Jablonski

Jean-Marc Claude Perrollaz

Guillaume Sevi

Thomas Nolwenn Emmanuel Delahaye

Cédric Michel Claude Chretien

Baptiste René Roger Batonnet

Noël Joseph Camille Robin

Thomas Etienne Camille Marie Van De Kerckhove

Pamela Dominique Danièle Reichert

Marie-Charline Stéphanie Charbonnier

Alain Marc Bromann

An axial turbomachine comprising a compression device with a variable-orientation vane rectifier stage; a combustion chamber downstream of the compression device; a turbine device downstream of the combustion chamber; and a leak passage of air compressed by the compression device, between the compression device and the turbine device for cooling the turbine device; and where the rectifier stage is configured to modulate the section of the leak passage according to the orientation of the vanes of the stage.

Axial turbine engine, and rectifier stage with variable orientation vanes for an axial turbine engine

Disclosed is a compressor of a dual-flow aircraft turboshaft engine extending longitudinally along an axis X, the compressor comprising a low-pressure compressor, a high-pressure compressor and an intermediate casing axially connecting the low-pressure compressor and the high-pressure compressor, the high-pressure compressor comprising an inlet guide stator comprising a retaining ring, an outer high-pressure compressor casing and a plurality of vanes, the compressor comprising an immobilising device comprising at least one first member secured to the intermediate casing and at least one second member secured to the retaining ring and configured to cooperate with the first member in order to prevent tangential movement while allowing axial movement and radial movement of the retaining ring relative to the intermediate casing according to the axis X.

Aircraft turboshaft engine compressor comprising a device for immobilising a retaining annulus

A sub-assembly of a turbine engine including a shaft, a bearing for guiding an axial end of the shaft, a nut which is screw-connected to the end of the shaft and a member for blocking the rotation of the nut in relation to the end of the shaft, wherein the member for blocking the nut includes a first section bearing a plurality of flexible tabs, one end of each tab of which cooperates with a radially inner annular wall of the end of the shaft and includes a second section which cooperates with the nut, characterised in that the second section of the blocking member is screw-connected to the nut and the features of the thread between the blocking member and the nut are different from the features of the thread between the nut and the end of the shaft.

Sub-assembly for mounting a guide bearing of a compressor shaft

The present disclosure relates to a control device of an annular row of variable-pitch vanes for an aircraft engine. The device may include an annular row of actuating levers which each may include a first end attached to a pivot of one of the vanes and a second end connected to a control ring in rotation about an axis of rotation. The control ring may include at least one annular series of articulated links, wherein the second end of each lever carries a pivot connection articulating two successive links of the annular series about a single axis, the single axis extending in a direction substantially parallel to the axis of rotation.

Control device of an annular row of variable-pitch vanes for an aircraft engine

An assembly for the control of variable pitch blades. The assembly includes a movable part movable parallel to an axis is in engagement with pivot connections which rotate about at least one radial axis fixed with respect to the casing, and which act on a radial shaft, which passes through a clevis fixed with a control ring to rotate with it about said axis. The radial shaft is mounted radially rotating with respect to the control ring and the casing.

Assembly for controlling variable pitch blades

Variable-pitch blade control ring () for a turbine engine, including an annular body () configured to be mounted so as to be rotatable about an annular casing () of the turbine engine. The body links to levers () for connecting to the vanes. The ring has a mechanism for guiding in an axial and/or helical direction, supported by the body. The mechanism includes at least one substantially radial finger () for axial abutment on at least one first surface () of the casing and for sliding on the surface.

Variable-pitch blade control ring for a turbomachine

The invention relates to a system for controlling variable-setting blades () for a turbine engine, which includes at least one control ring () mounted rotatably mobile about an annular casing () with axis of revolution A, at least one annular row of variable-setting blades () extending substantially radially relative to said axis A and connected to said at least one control ring so that a rotation of the ring about the casing rotates the blades about substantially radial axes B, and means () for actuating said at least one ring in order to rotate same about the casing, characterised in that said actuation means are connected to said at least one ring by linking means comprising a shaft () extending along an axis C which is substantially radial relative to said axis A and mounted rotatably mobile about said axis C on the housing.

System for controlling variable-setting blades for a turbine engine

An assembly for controlling variable pitch vanes in a turbine engine, the assembly comprising an actuating ring surrounding a casing of the turbine engine and connected by rods to variable pitch vanes. The actuating ring is configured to rotate around the casing. The assembly further includes a passive element including a first end sliding connected to a second end. The first end is connected by a sliding pivoting link on the actuating ring, and the second end is connected by a ball-joint link to the casing.

Assembly for controlling variable pitch vanes in a turbine engine

The invention relates to a system for controlling variable pitch blades for a turbine engine, comprising an annular row of variable pitch blades extending about an axis (A) and each comprising a blade connected at the radially outer end thereof to a pivot () that defines a substantially radial axis of rotation of the blade and which is connected by a lever () to control means (,) extending about said axis. The invention is characterized in that said control means include first links () supported by said pivots and second links () extending between said first links, said first and second links extending substantially along a same circumference of said axis and being connected to one another and to actuation means ().

System for controlling variable pitch blades for a turbine engine

A system for controlling variable-pitch vanes for a turbine engine, including a control ring having an axis of revolution and, about the axis of revolution, an annular row of connecting rods for connecting the ring to the vanes, each connecting rod including a first end designed so as to be connected to one of the vanes, and a second end which is connected to an elongate shaft which is connected to s the ring. The shaft connected to each connecting rod has an axis of elongation which is inclined relative to a plane extending substantially through the axis of revolution and the connecting rod.

Growing community of inventors

Moissy-Cramayel, France

Lilian Yann Dumas