Safran Aircraft Engines

Snecma

Olivier Bazot

Jérémy Philippe Pierre Edynak

Guillaume Pascal Jean-Charles Gondre

Olivier Belmonte

Vincent Joudon

Clément Cottet

Stéphane Roger Mahias

Clémentine Charlotte Marie Mouton

Matthieu Pierre Michel Dubosc

Guillaume Claude Robert Belmon

Charles-Henri Claude Jacky Sullet

Jeremy Philippe Pierre Edynak

Fanny Marie Libes

Jérémy Edynak

Farhana Hussain

Jeremy Edynak

A blade () of a fan (), made of composite material, of a turbomachine. On a portion () of the blade () which extends from a lower limit () located at a predetermined distance (d) from the shank () of the blade equal to at least 80% of the predetermined height (h) to the top () of the blade (), a dihedral angle (D) measured at least one predefined point on the chord of the blade (), located on the chord of the blade () at the upstream end () of the nose () of the shield (), is greater than or equal to −3° and less than or equal to 0°.

Fan blade with zero tip dihedral at the head

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

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

A method for manufacturing a blade from composite material having an added metal leading edge for a gas turbine aeroengine includes producing a blade body from composite material including a blade root part, a shank part and an airfoil body part; manufacturing, via additive manufacturing, a leading edge extending in a longitudinal direction between a lower end present at the shank part of the composite material and an upper end present at the tip; bonding the manufactured leading edge onto the foremost edge portion of the airfoil body of the blade body.

Blade made of composite material with variable-density attached leading edge

An interface member equips a control ring of a high-pressure compressor of an engine. This control ring has at least one housing intended to partially house a guide shoe. This interface member includes a central wall to which two holding tabs are secured, delimiting a through-housing having dimensions substantially identical to the initial dimensions of the housing, and suitable for being inserted into the housing, after it has been machined to receive same following a deformation, until the holding tabs keep it stationary relative to the control ring.

Interface member for reconditioning a control ring of an engine compressor, and associated reconditioning method

A control assembly for a stage of variable-pitch vanes for a turbine engine generally includes an actuating ring having an annular body, a vane guidance means for connecting to the cylindrical pivots of the variable pitch vanes, a rotating means for rotating the actuating ring about a casing of the turbine engine, and a centering means for cooperating with the casing to center the actuating ring. The centering means may have at least one skid bearing against the casing. At least one of the skid or the rod may be configured to cooperate by radial sliding with an inner wall of a housing. The skid may be configured to be mobile during operation by sliding between a radially internal position and a radially external position.

Control assembly for a stage of variable-pitch vanes for a turbine engine

A turbo-engine module comprises a turbo-engine housing, and a thermal protection shell of the housing. The thermal protection shell is configured to cover at least partially the housing in order to protect same thermally. The module comprises a wear protection strip which is situated between the housing and the thermal protection shell, in a junction region of the housing and the thermal protection shell.

Turbo-engine housing, equipped with a thermal protection shell and an anti-wear strip

A device for controlling variable-pitch turbomachine members such as stator vanes, wherein the movement of a control mechanism is imparted to a ring that rotates the levers for pivoting the vanes about a stator, and takes place with a possible change in the length of the bottle screw connecting the ring to the control mechanism, thereby allowing the blade pitch angle law to be changed according to the extension of the control device. A greater freedom of adjustment is thus obtained. The device can be useful when a single control mechanism is used for multiple rings arranged side by side, making it possible to have different control laws for the rings.

Device for controlling variable-pitch members in a turbomachine

A control ring for a stage of variable-pitch vanes for a turbine engine includes at least one member for bearing on a casing and means for fixing the member. The member includes a bushing with an axial bore for the passage of the member or an element for supporting the member. A through-slot opens into the bore and allows for substantial radial deformation of the bushing. The member further includes an outer thread for screwing the bushing into a complementary thread of a hole in the body, thereby deforming the bushing. The member or support can be mounted and moved inside the bore, to a second position, in which the bushing is radially constrained and is tightly mounted on the member or support, which is thus immobilized in relation to the bushing.

Control ring for a stage of variable-pitch vanes for a turbine engine

A flexible metal foil can be fixed on the inside part of a variable pitch vane control ring of a turbojet compressor, so as to close all through holes in which lever pins and their surrounding bushes are housed. As a result, the foil can retain the shank of the bush if the bush breaks. The use of such foil does not impose the development of a new model of control ring and its impact on the mass is small enough so that it does not affect engine performances. Therefore it avoids problems related to the breakage of bushes without having to make major changes to the existing system.

Growing community of inventors

Moissy-Cramayel, France

Olivier Bazot