Safran Aircraft Engines

Clément Cottet

Régis Eugène Henri Servant

Vivien Mickaël Courtier

Vincent Joudon

Laurent Jablonski

Thierry Georges Paul Papin

Christophe Marcel Lucien Perdrigeon

Olivier Belmonte

Gilles Alain Marie Charier

Adrien Jacques Philippe Fabre

Christophe Paul Jacquemard

Olivier Bazot

Sébastien Emile Philippe Tajan

Jean Charles Olivier Roda

Ceddric Beljambe

Clémentine Charlotte Marie Mouton

Jean-Claude Christian Taillant

Arnaud Langlois

Kevin Franck Jacques Tribout

Mathias Gautier

Fabrice Michel François René Cretin

Leny Toribio

Disclosed is a variable pitch propeller blade for an aircraft turbine engine. The blade includes an airfoil connected to a root, the root having a body housed in an annular barrel that extends around a pitch axis of the blade, the body including a free end opposite the airfoil; a shoulder towards the airfoil; and a bulb located between the free end and the shoulder. The bulb can have a cross-section, referred to as the middle section, that has a maximum value Sm, and the barrel can be affixed to the body and covers and matches at least a portion of the bulb and the shoulder.

Aircraft turbine engine comprising variable-pitch propeller vanes

An assembly for an aircraft turbine engine is provided. The assembly generally includes an un-ducted propeller blade of which the root has a bulbous portion; a system for setting the pitch of the blade about a pitch setting axis, the pitch setting system including a cup configured to be placed inside the outer casing, has a flared open top end for axial insertion of the root and in which the root of the blade can be axially affixed by a locking member; and at least one radial retention prong in a radial space reserved between the wall of the cup and the root.

Assembly comprising a vane and a vane pitch setting system

An assembly for a propeller of a turbine engine of an aircraft is provided. The assembly includes a variable-pitch vane having a blade connected to a root, the vane having a longitudinal axis aligned with a vane pitch axis which passes through the root, a base rigidly connected to the vane to rotate together with the vane about the axis and connected to a portion of a toothed wheel extending around the axis, and a counterweight device having a shaft which can rotate about an axis substantially perpendicular to the axis, the shaft being connected to at least one flyweight and to a pinion meshed with the toothed wheel portion. The toothed wheel portion can be attached to the base by at least one shear pin.

Propeller for a turbine engine of an aircraft with a variable-pitch vane and a geared counterweight device

A system for controlling the pitch setting of a propeller blade for an aircraft turbine engine, includes a blade having a vane connected to a root. A hub accommodates the root of the blade, and a ring is mounted around the root and in the hub. Stops are also mounted around the root and in the hub. A nut is threadedly engaged with a thread of the ring and is configured to bear axially against the hub to secure the assembly.

System for controlling the pitch setting of a propeller vane for an aircraft turbine engine

An unducted rectifier for a turbomachine is provided. The rectifier includes: (1) stator vanes each having a root and a blade radially projecting from the root, the root having two half-platforms; (2) pivots, each associated with a vane mounted so as to pivot about a pitch axis and configured to connect to a system for changing the pitch of the blades, each pivot having an upper platform and a cylindrical lower portion; and (3) attachment systems for attaching the half-platforms of the root of the vane to the associated pivot, each having two plates having a substantially identical shape to each half-platform and a clamping system for clamping the half-platforms between the plates of the attachment system and the upper platform of the pivot.

Unducted rectifier for a turbomachine, turbomachine module and aircraft turbomachine

The present invention relates to a vane () of a turbine engine, comprising: —a structure which has an aerodynamic profile (); —a spar () comprising a vane root portion (), a blade portion () arranged inside the structure which has an aerodynamic profile (), and a stilt portion (), the blade portion () comprising a body () connected to the vane root portion () and two arms extending radially from the body (); and —a structural reinforcement () extending from the vane root portion () to the body () of the blade portion (), the structural reinforcement () being rigidly connected to the vane root portion () and configured to form a force path separate from the stilt portion () in the event of failure of the spar () within the stilt portion ().

Vane comprising a structure made of composite material, and associated manufacturing method

A system for controlling the pitch of a propeller blade for an aircraft turbine engine is provided. The system generally includes a cup having an annular wall extending about a pitch setting axis of the blade, the annular wall having a lower axial end enclosed by a bottom wall, and an upper axial end that is open and configured so as to enable a root of the blade to be mounted in the cup; and a locking ring that extends around the pitch setting axis and is configured to be mounted around the root, the locking ring being a double dog ring that comprises two annular rows of outer dogs constituting active and safety dogs, respectively.

System for controlling the pitch of a propeller vane for an aircraft turbine engine

An assembly for an aircraft turbine engine is provided. The assembly generally includes an un-ducted propeller blade of which the root has a bulbous portion; a system for setting the pitch of the blade about a pitch setting axis, the pitch setting system including a cup, configured to be placed inside the outer casing, has a flared open top end for axial insertion of the root and in which the root of the blade can be axially affixed by a locking member; and at least one radial retention prong in a radial space reserved between the wall of the cup and the root.

A system for controlling the pitch setting of a propeller blade for an aircraft turbine engine is provided. The system generally including a blade having an airfoil connected to a root; a cup having an annular wall extending about a pitch axis of the blade and a lower axial end enclosed by a bottom wall; a locking ring that extends around the root and inside the cup; a safety element that ensures the retention of the root relative to the cup. The at least one safety element can have a generally elongate shape and can pass through aligned holes in the bottom wall of the cup and in the free end of the root.

An assembly including a propeller blade and a pitch adjustment system for setting the pitch of the blade. A root of the blade has a bulb and the pitch adjustment system for setting the pitch of the blade includes a cup having an upper opening; —a retaining ring, which extends around the bulb, is restricted at least in terms of axial movement towards the opening relative to the cup and has a bearing face to inhibit axial movement of the root towards the opening The pitch adjustment system being further includes a lower seat for the root to engage the cup, the seat and/or the retaining ring being mounted so as to be capable of axial translation relative to the cup by at least one clamping mechanism.

Aircraft turbine engine comprising variable pitch propeller blades

A system for controlling the pitch of a propeller blade for an aircraft turbine engine, including a cup having an annular wall extending about an axis intended to be a pitch setting axis of the blade, and a bottom wall configured so as to cooperate in a form-fitting manner with a free end of the root so that the cup is prevented from rotating relative to the root about the axis, and a locking ring that is configured so as to be mounted within the cup and to cooperate respectively with the root and the annular wall of the cup in order to ensure axial retention of the root in the cup.

Aircraft turbine engine comprising variable-pitch propeller blades

A turbomachine module with a longitudinal axis, the module comprising: a rotary casing rotatable around the longitudinal axis and arranged to carry a propeller provided with a plurality of blades; a system for changing the pitch of the blades of the propeller comprising: a control, and a mechanism for varying the pitch of the blades of the propeller connecting these blades to the control, wherein the control comprises a rotary actuator comprising a control body and a reference body which is integral with the rotary casing, and wherein the mechanism for varying the pitch comprises a synchronization ring which is driven in rotation around the longitudinal axis by the control body and which is guided in rotation on the rotary casing, the synchronization ring being connected to the blades.

Turbomachine module for a variable pitch blade propeller and turbomachine comprising it

A turbine engine is provided with a longitudinal rotation axis having at least one shaft with a radial axis, in particular a pitch change system for the blades of a propeller, said shaft traversing a radial passage of a substantially cylindrical case around the longitudinal axis. The turbine engine includes an annular oil guiding device around the radial shaft. The device has first and second annular parts nested in one another and secured to one another by hooping. The first part is secured by hooping to the radial shaft, and the second part is configured so as to be separated from the first part under the action of a force oriented along the radial axis and exerted on the second part by a member of the turbine engine forming a stop during a radial movement of the radial shaft.

Turbine engine with an oil guiding device and method for disassembling the turbine engine

The invention relates to turbine engine module () including a case () rotating around a longitudinal axis (X) and carrying a propeller having a plurality of blades, a stationary case () comprising a cylindrical wall () extending between an inner wall () and an outer wall () of the rotating case (), and a system () for changing the pitch of the blades () of the propeller. The wall () is connected downstream to a first frustoconical wall () and upstream to a second frustoconical wall (), a first rolling bearing () being inserted respectively downstream directly between a radially outer face () of the inner wall () and a radially inner face () of the first frustoconical wall, and a second rolling bearing (') inserted downstream directly between the radially outer face () of the inner wall () and an inner face () of the second frustoconical wall ().

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Melun, France

Clément Cottet