Safran Aero Boosters Sa

Techspace Aero S.a.

Techspace Aero

Alain Derclaye

David Depaepe

Angela Durie

Rodolphe Lebrun

Denis Bajusz

Xavier Wery

Enrique Penalver Castro

Philippe Ernst

Régis Dupuy

Mathieu Renaud

Philippe Berot

Kris Hoes

Sébastien Vacca

Assembly for axial turbomachine, in particular for an aircraft turbojet, the assembly comprising: an annular casing with an internal surface (); an annular row of stator baffles () with at least one stator baffle () comprising an airfoil () which extends radially from a fixing platform (), the fixing platform () being fixed to the casing and having a polygonal outline; characterised in that it further comprises a gasket () comprising a frame, the outline of which conforms to the polygonal outline of the fixing platform (), the frame being in radial contact with the fixing platform () and the casing in order to ensure a seal.

Assembly for axial turbomachine, associated axial turbomachine, assembly method, and sealing joint

A rotor for an axial turbomachine includes a drum formed of several parts including: composite rings made of composite material and metallic rings interposed between the composite rings. The metallic rings carry the rotor blades. The metallic rings have an axial branch axially overlapping the composite rings and at least one radial branch in contact with the composite rings.

Hybrid rotor with a segmented drum

A method for manufacturing a curved composite casing for a turbomachine, notably for a low-pressure compressor of an aircraft turbojet engine, includes the following sequence of steps: (a) draping a preform by automatic placement of carbon fibres on a concave form, referred to as a female form; (b) laying a glass-fibre ply on a convex form, referred to as a male form; (c) transferring the preform onto the convex form, covering the glass-fibre ply on the convex form. Step (b) laying includes a phase (&#x3b1;) of laying a metal strip and/or an epoxy profile on the convex form, then a phase (&#x3b2;) of covering the metal strip with the glass-fibre ply.

Method for manufacturing a composite casing for a turbomachine compressor

A composite external casing for a compressor of an axial-flow turbomachine, the casing comprising a generally circular wall having a matrix and a woven fibrous reinforcement. The latter is formed by a stack of fibrous plies having fibers woven according to a weft positioned in the axis of the circular wall, and a warp positioned around the circumference of the wall. The stack of plies comprising, depending on thickness, two external layers and one central layer. The layers include differences in the proportions between the weft fibers and the warp fibers. In the external layers the warp fibers make up the majority. In the central layer the weft fibers make up the majority. The stack exhibits interlayers inserted between the central layer and each external layer. The plies corresponding to the interlayers exhibit fibers woven at +45&#xb0; and &#x2212;45&#xb0; in relation to the axis of rotation of the turbomachine.

Composite casing for a compressor of an axial-flow turbomachine

The invention relates to an external composite housing for a compressor of an axial turbomachine, the housing having a generally circular wall with a matrix and fiber reinforcement. The housing includes a circular wall with an internal surface having a continuous curve around the circumference of the wall. The wall includes flat facets that are flush with the internal curved surface of the wall. The facets are arranged in annular rows to receive annular rows of stator vanes. The facets are flat disks against which the vanes bear to optimize the orientation of the vanes, while reducing the concentrations of mechanical stresses at the platform/wall interfaces.

Faceted housing for axial turbomachine compressor

The present application relates to the compressor stator of an axial turbomachine. The stator comprises an annular row of main stator blades and auxiliary blades each of which are associated with a main blade. The auxiliary blades are located at the trailing edges of the main blades and are in the vicinity of the pressure faces of the main blades. The auxiliary blades are aligned to generate a low-pressure area at the trailing edges of the main blades. Thus, a flow bypassing a main blade by its suction face is sucked in by the low-pressure area when it approaches the trailing edge of the main blade. Stalling is thus avoided and the efficiency of the machine is improved.

Axial turbomachine stator with ailerons at the blade roots

The invention relates to an angular sector of a bladed stator of a low-pressure compressor of an axial turbine engine. The sector comprises an outer shroud and an inner shroud in the form of circular arcs intended to be mounted in a concentric manner on the outer casing of the turbine engine compressor. The sector likewise comprises a row of stator vanes extending radially and anchored in the shrouds in such a manner as to form a bladed box. The vanes of the box comprise anchoring lugs at their outer ends, the lugs being disposed in the thickness of the outer shroud. The inner shroud comprises stubs for anchoring vanes.

Guide vane assembly vane box of an axial turbine engine compressor

The present invention relates to a turbine engine rectifier stage comprising a plurality of fixed vanes connecting an inner ferrule supportto an outer ferrule support, said inner ferrule support and said outer ferrule support defining an aerodynamic vein and comprising a set of contiguously assembled sectorsrespectively, the plurality of fixed vanes comprising so-called structural vanessurrounding so-called non-structural or aero vanesso as to form boxes, said structural vanesbeing rigidly attached to the ends of the sectors of the inner ferrule supportby means of attachment elementsin order to impart increased stiffness to the boxes

Architecture of a compressor rectifier

Setting in place of one or several coolers in the wall of a secondary flow of a bypass turbomachine. The wall extends from an intermediate casing toward a leading edge of a separator nose between a primary flow and the secondary flow. The wall includes a series of support arms attached to an intermediate casing, distributed over the perimeter of the wall and directed upstream. A series of surface air-oil heat exchangers forming wall segments are arranged end-to-end on the support arms, so as to form an annular wall. A shroud having a leading edge is arranged and fixed in the area of the upstream edges of the heat exchangers, so as to complete the wall. The support arms include hydraulic connectors connected to one another on each arm, adapted to cooperate with corresponding connectors in the area of the heat exchangers and in the area of the intermediate casing.

Integration of a surface heat exchanger to the wall of an aerodynamic flowpath by a structure of reinforcement rods

Guide vane stage of a turbine engine comprising a series of fixed blades connecting an inner collar to an outer collar, characterized in that said fixed blades comprise attachment platforms with flat surfaces that co-operate with a plurality of juxtaposed flat facets, the flat facets being located on the inner face of the outer collar in order to ensure attachment with a contact of a flat/flat type between the fixed blades and the outer collar.

Guide vane architecture

A platform for a bladed wheel of a turbomachine including a drum and blades of hammer-head attachment type, the foot of which is retained in a circumferential groove of the drum, having bearing and/or retaining faces cooperating with the drum is disclosed. The platform includes at least two openings spaced apart circumferentially and each able to receive the foot of a blade, whereby it constitutes a multiple-blade platform in the form of a piece separate from the blades.

Platform and blade for a bladed wheel of a turbomachine, bladed wheel and compressor or turbomachine comprising such a bladed wheel

Use of the stator blade platforms for the deposition of a track of adjacent abradable material inside an external turbomachine shell is disclosed. The stator blades are attached to the shell so as to define an annular edge that is substantially continuous and the abradable material is deposited using this edge to delimit a boundary of the track of abradable material.

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Couthuin, Belgium

Alain Derclaye