Safran Aircraft Engines

Vivien Mickaël Courtier

Vincent Joudon

Clément Cottet

Régis Eugène Henri Servant

Adrien Louis Nicolas Laurenceau

Adrien Jacques Philippe Fabre

Christophe Paul Jacquemard

Clément Pierre Postec

Dominique Gerhardt Mayhew

Laurent Jablonski

Thierry Georges Paul Papin

Anthony Binder

Paul Antoine Foresto

Dominique Gerhadt Mayhew

Jonathan Evert Vlastuin

William Henri Joseph Riera

Eddy Keomorakott Souryavongsa

Stéphane Roger Mahias

Teddy Fixy

Arnaud Langlois

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 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

Fibrous preform for a composite blade and also a composite blade formed by means of such a preform, a rotor and a rotating machine comprising such a blade, the preform comprising a first longitudinal section, configured to form a blade root, and a second longitudinal section, extending from the first longitudinal section, configured to form a portion of an airfoil, wherein the first longitudinal section has a first thickness at its upper end and wherein the second longitudinal section comprises at least one set-back zone having a thickness at least three times less than the first thickness, said set-back zone occupying at least 50% of the second longitudinal section.

Preform for a composite blade

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

The present invention relates to a blade comprising: —a structure made of composite material; —a blade root attachment part comprising a wall delimiting a cavity, a first opening formed in the wall and a second opening located under the blade root portion, the structure made of composite material extending through the first opening; —two locking parts configured to axially abut against a shoulder of the attachment part and to bear against the blade root portion; and —a cover for compressing the blade root portion against the locking parts.

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

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.

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

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

The present invention relates to a blower vane of a turbomachine, comprising a structure made of composite material which comprises a fibrous reinforcement and a matrix in which the fibrous reinforcement is embedded. The vane comprises a first rigidification insert which extends in a first direction and at least one second insert which is connected to the first in a second direction which is non-collinear with the first direction, the first insert projecting from the vane in order to be connected to a disc of a turbomachine element.

Blower vane

A blade includes a fibrous reinforcement having a three-dimensional weave densified by a matrix, the fibrous reinforcement including, in a single woven piece, a root and an aerodynamic profile part extending along a longitudinal direction between the root part and a blade tip portion and along a transverse direction between a leading and a trailing edge portion. The profile part includes first and second suction side and pressure side faces. The fibrous reinforcement includes a separation forming a housing inside the fibrous reinforcement, a bladder filled with a shaping foam being present in the housing. The separation extends over a separation zone inside the profile part of the fibrous reinforcement comprised between the root part and the blade tip portion in the longitudinal direction and between the leading and the trailing edge portion in the transverse direction. The separation opens to the outside of the profile part.

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Moissy-Cramayel, France

Vivien Mickaël Courtier