Safran Aircraft Engines

Vincent Joudon

Vivien Mickaël Courtier

Clément Cottet

Régis Eugène Henri Servant

Laurent Jablonski

Clément Pierre Postec

Thierry Georges Paul Papin

Franck Bernard Léon Varin

Christophe Paul Jacquemard

Regis Eugene Henri Servant

Mathieu Simon Paul Gruber

Anthony Binder

Fernando Gea Aguilera

Olivier Bazot

Damien Bruno Lamouche

Clement Cottet

Vivien Mickael Courtier

Matthieu Patrick Jean Roger Perlin

Arnaud Langlois

Pierre Antoine Bossan

Matthew Savage

Adrien Clément Marcel Dubois

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

The invention relates to a secondary flow stator vane () for a turbomachine, comprising skins () having end portions () delimiting an opening () and a cavity () therebetween, which skins diverge from one another in a direction (Y). A filler material () is located in the cavity () at a distance from the opening (). A reinforcement (), the density of which is higher than the density of the material (), comprises a first reinforcement portion () located in the cavity () against the material () and a second reinforcement portion () for closing the opening () between the portions () to form a single piece.

Secondary flow guide vane of a turbomachine and turbomachine provided therewith

The present invention relates to a blade comprising: a structure of aerodynamic profile comprising two mutually opposite skins; and a spar comprising a fibrous reinforcement obtained by three-dimensional weaving and densified by the matrix, the spar comprising a blade root portion extending outside the structure of aerodynamic profile and an airfoil portion arranged inside the structure of aerodynamic profile between the two skins. Moreover, within the blade root portion, the fibrous reinforcement of the spar comprises a non-debound region and at least two debound regions extending radially from the non-debound region so as to form at least four separate branches.

Blade comprising a structure made of composite material and associated manufacturing method

The invention relates to an assembly for a turbine engine blade, the assembly comprising a fastener defining a well for receiving a blade root, and a clamping device for clamping the blade root against the fastener when the blade root is received in the well, wherein the clamping device comprises: at least one clamping member suitable for bearing simultaneously on the blade root and on the fastener in the well so as to exert a clamping force on the blade root, the clamping member defining a threaded hole, and a resilient layer arranged to bear in the well on the blade root, a rod comprising a thread engaging with the threaded hole so that a rotation of the rod with respect to the clamping member causes a variation in the clamping force exerted by the clamping member on the root.

Fastening assembly for a turbomachine blade

The present invention relates to a blade () comprising: —a composite material structure (), —a blade root fastening portion () further comprising a shoulder () extending into the recess from the wall —a base () arranged in the recess and comprising a support member configured to abut against the shoulder () of the blade root fastening portion () and a passage () formed in the support member, the sections () of the blade root portion () of the composite material structure extending through the passage (), and —a blocking part () arranged in the recess between the two sections () of the blade root portion () such that each section of the blade root portion () is pressed against the support member by the blocking part ().

Blade comprising a composite material structure and associated manufacturing method

An unducted fan having variable pitch blades for an aircraft or wind propulsion system is described. The fan includes a hub provided with housings pivotally receiving vanes about radial axes, and an outer casing of the hub into which circular openings of the housings open. Each vane includes a root which is rotatably mounted in the associated housing, a radially oriented blade and a disc-shaped platform extending from the blade to an edge of the circular opening. The blade includes at least one skin which includes a free lower edge facing the side of the root, wherein the platform is attached to the free lower edge of the skin.

Unducted fan having variable pitch blades comprising reduced disturbance platforms

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.

An assembly comprising a propeller blade and its system for angularly adjusting the pitch of the blade including a bowl which is radially delimited by an annular wall extending about an axis for adjusting the pitch of the blade, the bowl having a bottom wall, a free lower end of the root being fitted axially into a complementary housing of the bottom wall in order to rotatably connect the bowl and the blade about the pitch-adjustment axis. The root of the blade comprises a first limiting face that engages with a first abutment face of the bowl to limit the rotation of the blade in the event of breakage of the lower end of the root.

Aircraft turbine engine comprising variable-pitch propeller blades

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.

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

The present invention relates to a fan rotor with variable pitch blades, comprising a rotor disc, equipped at its periphery with a plurality of rotary fasteners (), each fastener () comprising a cell () for receiving the root () of a blade (). This rotor is characterised in that an elongated wedge () and a prestressing rod () with at least one cam () are also arranged in each cell (), the bottom of the cell () comprising as many retraction cavities () as the rod () comprises cams (), in that the prestressing rod () is interposed between the wedge () and the bottom () of the cell (), so that said cam () is facing a corresponding retraction cavity () and in that the prestressing rod () can rotate about its longitudinal axis (X-X′), between a rest position, in which the cam () is housed in the retraction cavity (), and an armed position, in which the cam () exerts a radial pressure on the central region () of the wedge () so as to move the wedge () towards the blade root ().

Fan rotor with variable pitch blades and turbomachine equipped with such a rotor

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.

Growing community of inventors

Moissy-Cramayel, France

Vincent Joudon