The invention proposes a turbomachine compressor blade (10) of radial overall orientation with respect to the main axis of the turbomachine the blade (10) comprising a radial internal root part (12) a radial external tip part (14) and a radially intermediate part (16) characterized in that the blade (10) comprises a...

The invention relates to an annular combustion chamber comprising inner and outer walls forming surfaces of revolution that are connected together upstream by an annular chamber end wall having injection systems passing therethrough, each injection system comprising at least 10 one swirler for producing a rotat...

An assembly comprising a turbine stator ring (5) and an annular ring support strut (1), the assembly further comprising, on a first side of the ring and the strut, hooks (4, 6) for assemblaig the ring to the strut and, on a second side of the ring and the strut axially opposed to the first side, sea...

The invention relates to a method for assembling a first turbomachine part with at least one second turbomachine part. The assembly method comprises the following steps: injection of a vulcanisable elastomer preferably a silicone (145) that can be vulcanised at room temperature known as RTV silicone in an injection ...

The invention relates to a device for dismantling a blade from a turbine said turbine comprising a set of blades said device comprising: a holding element (11) comprising: a blocking surface (111); a dismantling opening (112);  means of attaching the holding element (11) to a shaft of the turbine the attachment mean...

The present application relates to a tool for holding a turbine engine part in order to attach a metal element (32 34) onto said part said tool including a first means (102 104) for immobilising the part and a second means for positioning the element (32 34) on a surface of the part said second means being removable...

The present invention relates to an abradable coating for a turbine engine part characterized by the fact that said coating includes a layer made of an abradable material the surface asperities of which are filled with thermally bonded ceramic grains forming a smooth free surface having a low roughness. ...

A tool for degritting a turbomachine. The invention concerns a tool for degritting a turbomachine such as a turbojet of an aircraft comprising at least one endoscopic viewing device (5) comprising viewing means (9) and a pipe (11) in which light guide and image transmission means are mounted a suction device (9) com...

The invention relates to a method for assembling two blades (21 23) of a turbomachine nozzle comprising: positioning of a first surface (20) of a first blade (21) and a second surface (22) of a second blade (23) facing one another said first (20) and second (22) surfaces being spaced apart from one another by an ass...

The invention relates to an annular combustion chamber of a turbomachine comprising two coaxial walls one internal (18) and one external (20) of revolution connected at the upstream end by an annular combustion chamber end wall through which there pass injection systems each comprising an injector and at least one s...

The invention relates to a nickel alloy derived from René 125 but with reduced levels of certain elements (Zr B P S Si and to a lesser extent Ti and Hf) in order to limit the appearance of cracks upon solidification in a moulding process. Specifically 4.80 % = Al = 5.00 % 1.48 % = Hf = 1.52 % 2.28 % = Ti = 2.33 % 0....

The invention pertains to the field of foundry and more particularly relates to a model (12) for lost model foundry in the shape of a turbine engine blade having a base (15) and a body (14) separated by a platform (20) substantially perpendicular to a main axis of the blade. The blade body (14) has a lower surface (...

System (20) for the emergency starting of aircraft turbomachines comprising at least one solid fuel gas generator (22) an electrically operated ignition device (24) a computer (28) connected to the ignition device and at least two independent starters (18) each one intended to start a turbomachine each starter compr...

Combustion chamber module for aircraft turbomachine comprising an annular combustion chamber in which each of the primary (62e) and dilution (64e) orifices in the outer annular wall (14) which is located at least partially in the wake (54) of a fuel injector (22) has a coefficient of discharge higher than that of it...

The invention relates to a vane (10) for a turbine engine, made of a composite material including a fiber reinforcement obtained by means of three -dimensional weaving of threads and densified by a matrix. The vane includes a blade (12) and a vane base (14) that form a single part , the vane base having two substan...

The invention relates to an impregnation mandrel for the production of a gas turbine casing made from composite material comprising: a mandrel (100) having a central wall (102) and two side plates (104a 104b); compaction bars (106a 106b) each including (i) a wedge (108a 108b) intended to bear against the fibrous rei...

The invention relates to the field of casting, and more particularly to a shell mould (1), and also to methods for manufacturing and using such a shell mould (1). This shell mould (1) has a central cylinder (4) , a plurality of moulding cavities (7) that are arranged in a cluster around the central cylinder (4) and ...

A device (8) for locking a root of a rotor blade in a groove in a rotor disc of a turbomachine comprising:  a circular ring sector (81) designed to be mounted transversely to the axis of the turbomachine in a groove in the rotor disc;  at least one locking wedge (82) which is rigidly secured and perpendicular to the...

COMBUSTION CHAMBER FOR A TURBOMACHINE INCLUDING IMPROVED AIR INLETS A combustion chamber (10) for a turbomachine, including two coaxial walls including air inlets, each of which is configured such that its orthogonal projection (44p), in a plane passing through the axis (28) of the injection system (20) closest to...

The invention relates to an impeller for a turbomachine such as a turbojet engine or a turboprop engine of an aircraft having a rotor disk (50) comprising at the outer periphery thereof ribs (14) defining cavities (18) for the axial mounting and radial retention of blade roots. An annular spoiler (48) comprises an a...

The electric thruster in question comprises at least one electric motor (10) a system for supplying power to said motor (10) comprising a high pressure tank (1) of ionizable gas a low pressure buffer tank (2) connected to the high pressure tank (1) by a valve (5 6) and a system of pipelines for conveying the gas fro...

The invention relates to a hollow vane ( 110) comprising a blade extending in a longitudinal direction (R-R"), a root and a head, an internal cooling passage (24) and an open cavity delimited by a bottom wall (26) and a flange (28"), and cooling channels (132) Connecting said internai cooling passage (24) and the...

The invention concerns a method for surface marking a mechanical part with a predefined graphic representation, comprising the application , via a laser source, of a single laser pulse onto an outer surface of a part to be marked , including interposing a mask having a predefined graphic representation between the l...

The invention relates to a method and a System for dynamically locating a fault (33) observed on a defective component (lt) in relation to a forging opération, comprising: - processing means (15) for modelling an opération of forming a component (1) by forging using a set of successive models (21a-21f) of said compo...

The present invention relates to a method for differentiating control failures in a system for controlling an actuator (14) determining the position of a member for modifying the state of a gas- turbine engine , the system including a single- or dual- channel electric control and a mechanical control , the electric ...

The invention relates to a turbine engine vane including a blade extending axially between a leading edge and trailing edge and radially between a base and an apex. The leading edge of the blade has a sweep angle that is positive continuously increasing from the base to a first radial blade height (hi) located betw...

The invention relates to an acoustic protection device (4) for an aircraft turbomachine fan casing comprising an acoustic protection panel (6) forming a shell ring sector centred on a central axis (2) the device also comprising one or more vibration damping strips (10) pressed firmly on one side against the exterior...

Method for reshaping a turbomachine blade (2) comprising at least one deformed zone (Z) the method involving acquisition of a profile of said blade comparing said profile against a reference profile in order therefrom to deduce at least one deformed zone (Zj) of the blade (2) comparing the deformed zone (Zj) against...

In a fiber structure woven into a single part by means of three dimensional weaving first woof threads connect therebetween warp thread layers from a first portion (1) of the fiber structure (10) which are adjacent to a disconnection (16) with warp thread layers from a second portion (14) of the fiber structure whic...

The invention relates to a method of manufacturing a part , involving the following steps: (a) providing a material in the form of powder particles (60), (b) heating a first quantity of the powder to a temperature higher than the melting point TF of said layer using a high energy beam (95) and forming , at the surfa...

The method of manufacturing a ceramic core for a blade comprising a lower part forming a core body an upper part forming a squealer tip recess and a set of rods for holding the upper part and the lower part together comprises: · a step of coating the rods with a material that has a flash point below 1000°C; · a step...

The present invention relates to a method for forming a protective coating containing aluminum on the Surface of a metal part wherein said part is contacted with a carburizer made of an aluminum alloy, at a treatment temperature and in a chamber, the atmosphere of which contains an active gas which reacts with the c...

The method according to the invention for estimating a thickness of a ceramic thermal barrier coating that is to be physically deposited in vapour form by a target onto a hot part of a gas turbine mounted on a support tool comprises:  a step (E10) of digitally modelling the geometric shape of the hot part and its ki...

The invention relates to a method for manufacturing a turbine engine blade root made of a composite material including a fibrous reinforcement compregnated by a mould , the method including forming one central fibrous strip (102) and two outer fibrous strips from three sets of layers of threads (Cio to C») connected...

The present invention relates to a shell mould (200) for manufacturing aircraft turbomachine bladed elements using the lost wax moulding technique and comprising:  shell mould bladed elements (1b) comprising a blade portion (2b) situated between a first end part (4b) delimiting the impression of a platform (8b) and ...

Turbomachine rotor blade having at its distal end (310B) a shroud (314) this shroud (314) comprising: a platform (320) delimiting the exterior surface of the flow path for the gases passing through the turbomachine and having opposing first (351) and second lateral edges; and upstream and downstream rubbing seals (3...

The invention relates to a method of manufacturing a p section reinforcing piece (10) made of composite material the method involving using three dimensional weaving to create a first set of layers of threads which layers are joined together to form a first fibrous rough form part (102) intended to form a base prefo...

A gas turbine housing (100) made from an organic matrix composite material comprising a reinforcement densified by an organic matrix delimits an inner volume. The housing comprises on the inner face (101) of same a structural portion (120) having a first face (120a) facing the inner face of the housing and a secon...

A linear seal (10; 10 ) of an inter blade platform having a length comprising a linear base (12; 12 ) intended to be secured to the inter blade platform (40) and a linear lip (14; 14 ) extending from the linear base (12; 12 ) said linear lip (14; 14 ) having a linear distal end portion (14a) configured to come into ...

The present invention relates to a method for manufacturing a metal component using the lost wax casting method the component being made of nickel alloy with a columnar or monocrystalline structure with at least one cavity of elongate shape comprising the following steps of creating a wax model (20) of the component...

A turbomachine casing (52) forming a continuous annular ring extending over 360° around a bladed wheel and serving as a propagation medium for rotating waves, each rotating wave being generated by two standing waves of the same frequency, and the casing including at least one longitudinal stiffener (50) at its outer...

The invention relates to a piston (1) having a first face (11), a second face (12) opposite to the first face (11), a third face (13) connecting said first and second faces (11 and 12) together and presenting a groove (30), and a sealing gasket (40) housed in said groove (30). The piston (1) includes a duct (50) con...

The invention relates to an injection mold for producing a model of a turbine engine blade comprising a top surface that folds onto a bottom surface both surfaces having long rods for supporting a core (2) for generating cooling cavities inside the blade wherein said long rods of the bottom surface are to contact a ...

The invention relates to a turbine engine such as an aircraft turbojet or turboprop engine comprising an annular combustion chamber defined by an inner shell (3) and an outer shell (4) a turbine distributor (2) arranged downstream from the combustion chamber (1) the downstream end of the outer shell (4) and/or the i...

The invention relates to a turbine engine blade the airfoil of which extends radially between a blade root and an airfoil tip axially between a leading edge (2) and a trailing edge (3) and tangentially between a pressure side and a suction side (5) the profile of said blade consisting of a series of basic profiles i...

The invention relates to an ignition unit (200) for a turbojet engine said unit comprising: an electrical power supply (201) a single control channel (202) to receive a control signal from a computer a main sparkplug ignition channel (210) to energize at least one main sparkplug of a main combustion chamber and an a...

The invention relates to a process for manufacturing an electrolytic bath for the production of a platinum based metallic sublayer on a metallic substrate which comprises the following steps: a) a first system comprising ligands and amine functional groups is provided said first system consisting of an aqueous solut...

The invention concerns a group consisting of a unit of a first piece (100) with a first portion (120)which is a tube which extends along an X axis, said first portion (120) being bordered laterally by a surface side (130) and having a proximal portion (122) that extends through an intermediate portion (124) whic...

The invention relates to a device for coupling shafts, comprising a coupling part intended to be fitted concentrically into a complementary coupling part said coupling part, comprising two centring zones between which a plurality of splines extend, in which device the splines have a profile which is constant along a...

An assembly comprising an airfoil (20) for a bladed 5 wheel together with a platform, such airfoils in association with such platforms forming a bladed wheel. The platform surface as formed in this way presents a circumferential depression (40) between the leading edge of an airfoil at 60% of the airfoil going ...

The invention ralates to a fabrication method of fabricating a thermal barrier covering a superalloy metal substrate, said thermal barrier comprising at least an underlayer and a ceramic layer, the method being characterized in that the following step is performed: the surface state of the underlayer is smoothed by ...

A device for searching for defects on parts that are masked, such as turbine engine blades, the device comprising a tubular sheath (28), light-guide means for guiding light and image-transmission means for transmitting images housed inside the sheath, an 10 examination head (62) at the distal end of the sheath ...

The invention relates to the field of monocrystalline smelting, and in particular to a monocrystalline smelting mould (1) including at least one moulding cavity(7), a starter cavity (10) having at least one first inverted funnel-shaped space (10a), and a separate second pedestal shaped space (10b) at the bottom of ...

The invention relates to a device for producing or building up a metal part by sintering and laser fusion said device comprising a laser beam generator a means for deflecting said beam in order to scan the surface of the part (5) to be produced and a sintering pan (6) containing a metal powder (7) used to cover the ...

The method according to the invention comprises, during a phase (EO) of starting up the turbomachine :— a step (E10) of open-loop génération of a control (WF_OL) of the flow of fuel based on at least one pre-established law; and — a step (E20-E30) of closed-loop monitoring of at least one operating parameter of the ...

The cylindrical calibration head (1) for the drilling of a shaft (4), comprising three flûtes (20, 21, 22) arranged evenly around the circumference so that they are spaced one from the next by an angle of 120° with respect to a rotation with respect to the axis of the calibration head, the flûtes allowing for t...

The invention relates to a method for manufacturing an integral rotationally symmetrical part which includes producing a blank of the part around a cylindrical mandrel the blank including at least one fibrous structure made of composite ceramic fibres coated with metal followed by the diffusion welding treatment of ...

The present invention relates to a method for modelling a part (1) the method being characterised in that it comprises implementing using data processing means (11) of a piece of equipment (10) steps of: (a) parameterising a curve of class C1 representing the value of a physical quantity characterising said part (1)...

The invention relates to a method for manufacturing an assembly (11) including a plurality of blades (9) mounted in a platform (7, 8), wherein: the blades (9) are manufactured separately from the platform (7, 8), the blades (9) being finished after manufacturing; a mixture of metal powder and thermoplastic binder is...

A method for cleaning a turboshaft engine blade (1) comprising a superalloy body covered with a coating, in which the coating of the blade (1) is at least partially machined using a pulsed laser (3), at least the feed rate of the pulsed laser (3) and the pulse frequency of the pulsed laser (3) being parameterised...

The invention relates to a fueling device for fueling the thrusters of a launcher. In characteristic manner  the device comprises: • a ground module (20) comprising at least: a ground pipe (22); a ground valve (21); and a ground plate (26) provided with a ground passage (28); • an on-board module (30) comprisin...

This bracket (13) for auxiliary equipment of a device  such as cables or pipes  consists of a single metal plate which has been cut and then folded  forming elbow connections (19) between the console (18)  supporting means (10) for attaching equipment  a flange (14) for fastening to the device  and two intermediate ...

The invention relates to a device for holding a turbomachine blade for the purposes of machining comprising a holder (1) comprising at least one housing (5) in which at least one unit formed of two jaws (22 23) having an opening into which to fit a blade aerofoil is removably mounted. The unit comprises six support ...

The invention relates to a method for finishing the shape of a turbine engine blade by machining in which one area (8) is produced by smelting with a thickened portion said thickened portion forming a first surface (10) with the surrounding profile and the theoretical profile being defined by a second surface (11) c...

Cooling of a part of the fuel injector corresponding to a secondary circuit through fuel circulation with permanent flowrate of a primary circuit. The secondary circuit (19) is connected to a distribution chamber (30) perforated by a plurality of fuel ejection orifices and the primary circuit (17) comprises at leas...

A method of igniting a turbine engine (11) using a spark plug (1) comprising a first electrode, a second electrode and a semiconductor body between the first electrode and the second electrode, the semiconductor body having an exposed surface, the ignition method 10 comprising a step of generating a spark adjac...

A method of non-destructively inspecting a mechanical part consists in directing high energy electromagnetic radiation emitted by a source onto the part (12) for inspection and in picking up the radiation 10 that has passed through the part (12). A mask (28) that absorbs the radiation is interposed between the ...

The present invention relates to a joining device (10) comprising a clevis (22) and a connecting member (28), the member (28) pierced with a tehrough hole (30)being housed between a first and a second lug (26a, 26b) of the clevis, these lugs respectively having a first clevis hole (32a) and a second clevis hole (32b...

A welded assembly of combustion chamber elements. Two subassemblies (20, 30) of the combustion chamber are fabricated by butt-welding, and a first subassembly (20) has an intermediate connection ring (14) welded thereto suitable for performing final welding with the second subassembly (30).

The invention relates to a method for reducing the diameter of an opening (2), comprising a step of peening a perimeter (3) of the opening (2). The invention also relates to a method for correcting the permeability of a part (9, 10) comprising a plurality of openings (2) for allowing a gaseous fluid to pass thereth...

A gas turbine with contrarotating HP and LP turbines comprises an LP turbine (50) having a plurality of moving wheels (56) alternating with nozzles (52), the moving wheels of the LP turbine rotating in a direction opposite to the direction of rotation of the moving wheel of the HP turbine, and an inter-turbine casin...

The combustion chamber comprises a chamber endwall (16) perforated by at least one passage hole (62). An injection system is mounted so that it car. slide diametrically with respect to the passage hole (62). A deflector (50) is mounted on the chamber endwall. The deflector comprises a fitting ring (64) bearing first...

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Abstract Missing

A device for attaching ring sectors (20) around a turbine wheel (18) in a turbomachine, each of the ring sectors comprising at its upstream end a circumferential rim (44) being able to be held on an annular casing rail (48) by an annular locking member (50) , and at its downstream end a part (70) that can come to pr...

Device for cooling a turbine casing in a turbomachine, this turbine comprising several stages each including a nozzle assembly (18) formed of an annular row of fixed vanes (20) and an impeller mounted to rotate in a cylindrical shroud formed of ring sectors (34) fixed to the casing, and a cooling circuit compris...

The present invention relates to a method for evaluating the wall thickness of a hollow part, of the turbomachine blade type, at least at a point having a determined radius of curvature at this point, within determined ranges of radii of curvature and thicknesses, comprising the determination of impedance values of ...

The present invention relates to a propulsion gas exhaust assembly, in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator, comprising a duct and a nozzle, wherein said duct comprises a first cylindrical duct element (21) receiving the gases and communicating downstream with t...

The present invention relates to a propulsion gas exhaust assembly, in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator, comprising a transition element (21) emerging in two duct elements (22, 23} each communicating with an ejection half-nozzle (24, 26), wherein each of the...

The invention relates to an afterbody (15) for a turbojet engine comprising an afterburner casing (16) , a thermal protection liner (26) , and a diaphragm-forming assembly (40) interposed between the liner and the casing, this assembly defining a flow area intended to be traversed by a ventilation stream (34). Accor...

A method of depositing an anti-wear coating on a mechanical part by thermal spraying of the AC-HVAF type, said coating being made of a copper-based alloy containing 30% to 42% by weight of nickel and 4% to 6% by weight of indium.

The present invention relates to a suspension for suspending a jet engine on an aircraft strut, comprising a beam (10) having a platform (11) provided with means for fastening it to the said strut and arranged transversely with respect to the axis of the engine, first (20) and second (40) lateral links each connecte...

The invention relates to a disk/blade assembly for an aircraft engine compressor, comprising a disk (2) and a plurality of blades with hammer attachment (6) , each blade comprising a blade root provided with an upstream bearing surface (32) situated on a leading edge side of the airfoil and a downstream bearing surf...

The present invention relates to the field of blades, particularly fan blades, intended for turbojets, particularly of the aeronautical type. Its objective is to provide a fan blade the features of which will enable the number of fan blades to be reduced while at the same time providing satisfactory performance. A...

The assembly arrangement between an inner race 6 of a bearing and a journal 2 supported in rotation in this bearing comprises: - a journal annular groove 36 and a race annular groove 26 which interact to form an annular channel 52 when they are placed opposite one another, - a retaining ring 40 placed in the sai...

The present invention relates to a method for bonding a first part (31) made of a ceramic matrix composite to a second part (34), to a defined dimension (A), wherein an insert (32) is fitted onto said first part (31), said insert (32) protruding beyond said dimension (A), the insert (32) is machined until its surfac...

Device for guiding a stream of air entering a combustion chamber of a turbomachine, comprising a flow straightener (14) followed by a diffuser (16), one of the shrouds (40) of the flow straightener being formed as one with one wall of revolution (34) of the diffuser, the other of the shrouds (38) of the flow straigh...

The present invention relates to a turbine module for a gas turbine engine comprising at least one turbine disk (3) and a disk-shaped component (5) mounted on the turbine disk upstream relative to the gas flow, said module comprising a means of assembly to the compressor of said engine, wherein the component (5) is ...

A system for controlling two stages (1U, ~1U") dt variable-pitch stator vanes (14, 14") of a turbomachine, the system comprising a drive element (24) for turning the control ring (22) of one of the stages (10) via a leader member (26) pivotally mounted on the casing (12), a synchronization bar (30) for transmitting ...

Process for manufacturing a tubular component comprising an insert made of a metal matrix composite, within which ceramic fibers extend, characterized in that it includes a draping step, in which a bonded sheet (21) of coated filaments is draped around a metal mandrel (24), each filament comprising a ceramic fiber c...

The present invention relates to a turbomachine rotor, particularly to the attachment of the blades (2), particularly the fan blades, to a rotor disk (4). The invention relates in particular to a turbomachine rotor comprising a disk (4) the periphery of which has a plurality of slots (41), a plurality of removable ...

An assembly comprising a metal piece, a piece made of ceramic material, and at least one intermediate connection element assembled to each of said pieces by brazing, said intermediate connection element (10') being constituted by a deformable sheet presenting at least two flat zones (11, 12) brazed to respectiv...

Title of the invention Assembly by brazing between a titanium-based metal piece and a piece made of ceramic material based on silicon carbide (SiC) and/or on carbon The assembly comprises a stack structure made up of the following elements assembled together in pairs by brazing: the titanium-based metal piece (10)...

A system of attaching an injection system to a turbojet combustion chamber base. It comprises a deflector welded onto the chamber base. The deflector comprises an annular portion having an edge forming a retaining shoulder directed toward the front of the turbojet and the injection system comprises a collar on which...

An assembly between a metal piece (1) and a ceramic material piece (7) made of an SiC and/or C based ceramic material, the assembly being such that it comprises a stack structure comprising the following elements assembled together in pairs in this order, by brazing: • said metal piece (1); • a first i...

Device for limiting turbine overspeed in a turbomachine, the turbine comprising a rotor formed of disks mounted on a turbine shaft and carrying moving blades, stages of fixe dblades disposed between the disks of the rotor, and means for shearing the moving blades of the upstream disk of the rotor, these means being ...

The invention relates to a device for cooling slots in a turbomachine rotor disk, comprising a rotor disk (4) having a plurality of slots (10) and a flange (14). The device also comprises blades (2), each having its root (12) mounted in a respective slot, a retaining annulus (22) having one end (23) mounted against ...

The present invention relates to the manufacture of an integrally bladed disk, especially for a turbomachine rotor. It relates more particularly to a process for manufacturing such a disk by friction welding. The manufacturing process comprises the following successive steps: • arrangement of a plurality of blades...

The invention concerns a stationary ring surrounding the passage of hot gases (14) of a gas turbine, said ring being enclosed by a stationary annular housing (2) so as lo define an annular cooling chamber (26) wherein emerges at least one cooling air supply orifice (28), said ring consisting of a plurality of ring s...

A shim (20) for a turbomachine blade (14), the shim comprising two branches (20A) for coming against bearing surfaces (16A) of the blade rotor (16), and a base part (20B) interconnecting the branches. The shim presents, at least in its branches (20A), a multilayer structure having at least three layers (31, 32, 33) ...

A device for damping vibration of a retention ring for axially retaining turbomachine fan blades (16), the blades being designed to be mounted via their roots (14) on a rotary disk (10) having an annular flange (18) extending axially and provided with a plurality of radial crenellations (20) for coming into c...

The invention relates to a method of manufacturing a cast ceramic core (10) comprising at least one recess, particularly for partitions, for a turbomachine blade in particular, comprising the shaping in a mould of a mixture containing a ceramic particles filler and an organic binder, extraction of the core from the ...

The invention relates to a metal component comprising at least a first zone treated by putting layers beneath the surface thereof in compression. It is characterized in that it comprises at least a first layer put in compression by shot peening and a deeper subjacent second layer put in compression by laser shock pe...

The ceramic drill bit has a particular geometry and is very advantageously applicable to the very high-speed drilling of parts made of a composite, especially a carbon-fiber composite having an epoxy lesin matrix. The invention a.lso relates to a method for the highspeed drilling of composites. ...

A turbomachine comprising at least one Stirling cycle thermal engine which is mounted at the end of a radial arm (36) of the exhaust casing (24) and comprises a working chamber (40) located outside the primary (B) and secondary (A) flows, a displacing piston (42) associated with a moving element (44) of an energy ge...

A turbomachine moving blade without a top platform, the blade including a fastener root (110) surmounted by an airfoil (112) that presents an end face (114), a pressure-side face (116), and a suction-side face, said fastener root and said end face being situated respectively at bottom and top ends of the blade that ...

A method for welding two metal parts, in which: the metal parts are positioned against each other in a welding position, the parts being respectively in surface contact along their welding surfaces, at least one of the parts having at least one extra-thick zone along its welding surface; TIG welding is carried out...

The invention relates to a fan platform (40) of a bypass turbomachine having a primary stream and a secondary stream. The platform (40) defines a portion of the surface of the nose around which the primary stream flows and that carries blades (30) extending radially outwards from said platform. Between two adjacent ...

The invention relates to a method of manufacturing a composite turbomachine blade, the method comprising the following steps: a)making a preform by three-dimensionally weaving yarns including tracer yarns disposed at least at the surface of the preform; b)cutting out said preform so as to leave intact a series of ...

The present invention relates to a lever for rotating about its pivot a turbomachine variable-pitch stator vane comprising three zones: a first zone for attachment to a lever drive member, a second zone for attachment to said variable-pitch stator vane, and a third zone of elongate shape between the first zone and t...

A method of inspecting the profile of the gfvJ -v"V zone between the cylindrical portion and the taper of a turbomachine part, the surface profile of the part being geometrically defined by at least one first zone corresponding to the taper of the part, at least one second zone corresponding to the connection betw...

The invention pertains to a method of detecting the variations of speed (R) of a rotor (2) characterized by the fact that it consists, in real time, in: measuring (1) signals (5) representative of the march-past of the teeth (6) of a phonic wheel (3) or of an equivalent means secured to the rotor (2) for a determ...

Fabricating a test blade including defects for calibrating a tomography installation for verifying similar blades. A three-dimensional blank (12) is made by weaving synthetic material fibers, and cavities (15) are created at predetermined locations in the blank before coating it in resin.

The invention concerns a method of recuperating a turbine element constituted of a substrate, forming the body of the element, and a protective coating adhering to the substrate. The method comprises the control of the turbine element in order to pinpoint the zones having a bonding defect between the protective coat...

See the attachment

A steerable structure (21, 27) of the catheter or endoscope type, the structure comprising an elastically or deformable longitudinal body (22, 28) including at least one actuator (16, 38) of material of the shape memory type incorporated longitudinally with the body (22, 28) together with Joule-effect heater means e...

The present invention relates to a bladed stator for a turbo-engine, in particular a bladed stator sector comprising an inner platform (3) and an outer platform (4), at least one blade (2) fixed between said platforms (3, 4) / at least one of said platforms (3, 4) comprising at least one flange (5, 6) having a first...

The present invention relates to a gas turbine engine, in particular in the aeronautical field, and is aimed at mounting a rotor shaft inside the engine. The operations of mounting and demounting a turbine engine are complicated owing to the number of parts which constitute it and of the small clearances between th...

A method of using ultrasound to inspect a part in immersion, by means of a focused beam of ultrasound waves oriented perpendicularly to the surface of the part, • BJIQI method consisting, when the axis of the focused beam is close to an edge of the part, in tilting the axis towards said edge relative to the normal t...

The method allows the mechanical characterization of a metallic material relative to a material constituting a part to be repaired and the validation of an installation for repairing said part by build-up welding with said metallic material. According to this method, a cavity is machined in a bar of said metal, the ...

Upsetting method of the invention for working a metal slug (1) of cylindrical shape and provided with a coating, is characterized in that the slug (1) is placed, lengthwise, in a sleeve (2) the internal wall of which leaves a space with respect to the lateral surface of the slug (1), the slug (1) and sleeve (2) asse...

The invention relates to a coupling (100) made of composite material comprising a polymer matrix reinforced by a fiber structure. The coupling comprises a structural portion (13 0) reinforced by a main fiber structure (30), and a first machining portion (120) reinforced by a first fiber structure (20) that is disti...

The invention relates to a standby lubrication method for an engine 1 in the event of the failure of a main lubrication system 2 of this engine 1, in which said failure is detected and, in response to the detection of this failure, at least one portion of a fuel fluid of the engine 1 is tapped off to lubricate at le...

The invention relates to a method of detecting damage in a bearing supporting at least one rotary shaft of an engine in rotation, the method consisting in: defining (SI) a measurement period corresponding to a range of speeds of rotation of the shaft during renewable activity at low speeds of operation of the engine...

The present invention relates to a tool for manufacturing a casting core, for a turbomachine blade with a leading edge and a trailing edge, the core (10) comprising a thick part on the leading edge side and a thin part (10A1) on the trailing edge side, comprising first and second dies (530, 540) of the core that can...

Method of manufacturing a turbomachine component that includes cooling air discharge orifices The present invention relates to a method of producing cooling fluid discharge orifices in the wall (171) of a part manufactured by the technique of lost wax casting in which a pattern of the part is produced in a wax mold...

A method of balancing a first turbomachine module (20), comprising along an axis of rotation a bearing plane (22) on one side and a junction plane (24) on the other, with respect to a rotor (I) comprising said module (20), in which an equivalent complementary module is defined such that the two modules form a rotor...

The bundle comprises two pairs of same-volume cylindrical tanks (11, 11), (12, 12), each pair comprising two tanks containing a same-density propellant suitable for flowing at the same volume flow rate, the four tanks being fastened directly to one another via reinforcing hoops (20) in such a manner that the center ...

A protection part (3) comprising at least two layers including an outer layer (7) and an inner layer (5) has its outer layer (7) made of an aluminum alloy that is reinforced with particles of SiC, the Sic particle content in said alloy lying in the range 15% to 40% by weight, while the inner layer (5) is made o...

The gastight sealing device associated with a functional clearance (20) existing between two sectors of a turbomachine comprises an annular plate (100) wound up on itself over at least one turn, covering said functional clearance (20).

Casing cover (10) in a jet engine, comprising two coaxial shells (36, 38) arranged one inaide uhe other and joiiied fixedly by radial envelopes (40) incdde which extend radial arma (2€) of the casing, the cover being faatened at its downstream end to an element of the casing and bearing axially at its upstream end o...

A system for controlling two stages (10, 10") of variable-pitch stator vanes (14, 14") of a turbomachine, the system comprising a drive element (24) for turning the control ring (22) of one of the stages (10) via a leader member (26) pivotally mounted on the casing (12), a synchronization bar (30) for transmitting t...

The invention relates to a method of using machining to repair a component workpiece (1), such as a turbomachine blade, from a known profile of the component (B), the method comprising a step of deforming (32) the profile (B) using a morphing method so that the deformed profile interpolates a cluster of points (A) m...

A method of inspecting the profile of the connection zone between the cylindrical portion and the taper of a roller for a turbo machine roller bearing. The surface profile is geometrically defined by a first zone corresponding to the taper of the roller, a second zone corresponding to the connection between the cyli...

The present invention relates to a turbomachine variable-pitch stator blade comprising an aerofoil (12), extended on one side by a pivot (14) by which it is mounted so as to rotate in a bore of the casing (3) of the turbomachine, and a plate (13), between the aerofoil and the pivot, perpendicular to the line formed ...

The present invention relates to a propulsion gas exhaust assembly in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator, comprising a duct (21) and a nozzle (24). It is noteworthy by the fact that said duct forms a vertical elbow.

The invention relates a process for manufacturing a ceramic foundry core having at least one thin region with a thickness "e", in particular in of a turbomachine blade trailing edge, comprising the forming in a mold of a mixture comprising a ceramic particle filler and an organic binder, the extraction of the core f...

The invention relates to an assembly for the mounting of the foot (121) of a blade, fixed or movable, of a turbomachine, made of metal, in the aperture (101) of a support made of metal, such as a casing, a fixed flange or the disk (10) of a rotor. Characteristically, this assembly comprises, between the foot (121) ...

The invention relates to a bipolar plate for a fuel cell, the plate being made up of two half-plates (200, 300) assembled one against the other via their inside faces (200a, 300a), each half-plate (200, 300) including in its inside face (200a, 300a) at least a first groove and a second groove (201, 202; 301, 302) th...

Shim (20) for a turbo machine blade (14), the shim having two branches (21A, 21B) suitable for wrapping around the flanks of the blade root (16), and having two tabs (22) each extending from one end of a respective one of the two branches, the tabs (22) being folded towards each other and being interconnected in suc...

A turbomachine exhaust casing with connection roots (24) between the structural arms (22) of the casing and the annular endplates (16, 18) of the hub (14) of the casing, said the roots having a profile that is optimized so as to reduce the level of stress in the connection portions, and thus increase the lifetime of...

The invention relates to a turbomachine combustion" chamber (202) comprising an inner annular wall (212), an outer annular wall (214) surrounding the inner wall so as to co-operate therewith to define an annular space forming a combustion area, a plurality of fuel injector systems (220) comprising pilot injectors (2...

Diffuser/guide vane assembly (10) for an aircraft turbojet or turboprop engine, the diffuser (12) comprising annular flanges (22, 24) joined by blades (26) and the guide vane assembly (14) comprising cylindrical shelves (28, 30) joined by vanes (32), the annular flanges and the cylindrical shelves being formed from ...

A system for ventilating a downstream cavity of an impellor of a centrifugal compressor in a turbomachine, this system comprising flow diversion means (70, 84) mounted fixedly in the downstream cavity (38) of the impellor (36) in order to divert the ventilation air taken from the outlet of the compressor (10) and ca...

System for cooling a downstream cavity of a centrifugal compressor impeller in a turbomachine, this compressor (10) being connected to a diffuser (12) comprising a downstream annular flange, an annular plating (70) being mounted coaxially around the flange of the diffuser and substantially extending over the entire ...

A turbomachine comprising a diffuser - distributor assembly comprising a downstream end-piece connected at its downstream end to means for injecting air for ventilating a turbine and delimiting with the impeller of a centrifugal compressor an annular cavity for the circulation of ventilation air taken from the outle...

The present invention is relative to a tool for rammer die-cutting an annular part comprising a lower insert holder with a lower die (122) cooperating with an upper insert holder and an upper die (132) , both dies comprising a die-cutting annular recess (122a, 132a) . The tool is characterized in that it comprises a...

The invention relates to a twin-spool gas turbine turbojet comprising a high-pressure rotor (1) and a low-pressure rotor, the low-pressure rotor shaft (2) being connected, at its upstream end, to a fan (10) housed in a fan casing (14), which turbojet comprises, upstream of the fan (10), a fixed cowl element (12) cen...

A turbine nozzle sector (110) that comprises an outer platform segment (102) and an inner platform segment (104) between which there extend one or more hollow vanes (106) . Each vane presents a trailing edge cavity (116) for feeding with cooling air and communicating with a plurality of vents (118) distributed along...

• san annular combustion chamber (40) with injection orifices (44); • a centrifugal compressor (10) having a centrifugal downstream stage; and • an annular diffuser (20) comprising: a radially- oriented upstream portion (21) with diffusion passages (22) connected to the outlet of the compressor; an elbow-shape...

Slotting milling cutter, comprising a carbide body (12) and a ceramic head (16) fixed by brazing to one end of the body, this head having teeth (22), each comprising a cutting edge (24) formed by an intersection between a front cutting face (A) and a lower flank face, in which the milling cutter has a frustoconical...

The invention relates to a turbomachine blade comprising an aerodynamic surface (12) made of a composite material and extending in a first direction (14) between a leading edge (16) and a trailing edge, and in a second direction between a root and a tip of the blade. The blade includes solid metal reinforcement (32)...

The present invention relates to a turbine stator of a gas turbine engine comprising a turbine casing (9), a turbine shroud ring (13) and a shroud ring support (11) connecting the shroud ring (13) to the casing (9). The stator is one wherein the support (11) is provided with an element that forms a heat shield posit...

The  invention relates  to a  turbomachine combustion chamber  (202)  having an inner wall  (212),  an outer wall (214)  surrounding the inner wall  so as  to  co-operate therewith to define a space  forming a combustion area,  a transverse wall  interconnecting the inner and outer walls,  and fuel  injection system...

The invention relates to a turbomachine blade comprising a plurality of blade sections (22) stacked along a radial axis (Z-Z), and in which the projection of a line (28a) interconnecting the leading edges of the blade sections of the bottom stack (28) onto a mid-plane presents a first longitudinal angle of inclinati...

A turbine stage in a turbomachine, the stage comprising a wheel mounted in a ring carried by a turbine casing, and a nozzle situated upstream from the wheel and including an annular fastener rim for fastening to the turbine casing, sealing being provided between the outer-rim of the nozzle and the upstream end of th...

The connection assembly of an arm (10) to a sleeve (11) is carried out substantially by parts of axes (21) crossing the arm and the spacers (26) between the parts of axes and the sleeve and the assembly bolts (32). The assembly and the disassembly are easy, even with highly reduced encumbrance, the connection is ...

The present invention relates to an impeller blade for turbomachine formed by molding, comprising a blade, at one end of which is provided a heel formed of a single piece with the blade, to which it is joined at the level of a connection area, the heel comprising a platform on which is provided at least one sealing ...

A woven fibrous structure embodied in one piece, used for producing a composite material part and comprising an internal part or a core (72) and a part adjacent to the external surface thereof or a skin (74, 76), is formed by three-dimensional core weaving with at least one weave selected from interlock and multilay...

The turbomachine blade (10) has ribs (50) formed in the vicinity of the trailing edge (42). Over the major fraction of the trailing edge (42), in zones where the temperature in operation is particularly high, the ends (53) of the ribs are closer to the trailing edge and/or the sections of the ribs (F) are greater. T...

A turbomachine  rotor assembly comprising:  a  rotor disk  (2)  presenting  slots  (4)  in  its  outer periphery; blades  (14)  fastened via their roots  (16)  in said slot (4);  and shims  (20)  mounted between the blade  roots  (16) and the disk  (2),  each shim  (20)  comprising two branches (20A)  and a base p...

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In a bypass turbomachine (10), at least one air takeoff orifice (34) is provided in the primary channel (24), said orifice leading to an air takeoff pipe (40) housed inside an air inlet sleeve (26) of the nacelle. The air takeoff pipe opens out in the vicinity of the pylon (32) into two air diffusion pipes (42) each...

Fabricating a test blade including defects for calibrating a tomography installation for verifying similar blades. A three-dimensional blank (12) is made by weaving fibers of synthetic material and elements (14) of resin in the solid state are inserted into predetermined locations in said blank prior to coating it i...

A turbomachine stator stage comprising two coaxial shrouds, respectively an inner shroud and an outer shroud with substantially radial vanes extending therebetween, the radially outer ends of the vanes being welded to the outer shroud and the radially inner ends of the vanes passing through orifices in an outer ring...

The method of the invention includes a step of digitally modelling a temperature measured by a sensor (10) by using a modeled signal (T2) a step of estimating a lag error signal for said sensor from the modeled signal (T2) and a signal (T3) obtained by filtering the modeled signal, the filter having as a parameter a...

The present invention relates to a turbomachine stator forming a stator vane ring or upstream guide vane element comprising a plurality of vanes (43) placed radially between a first inner ring (42) and a second outer ring (44), the two rings being concentric, the second ring having a cylindrical outer surface portio...

The present invention relates to a variable-pitch vane (8) for a stator stage, including an active part of the vane (43) either side of which are positioned a radially inner platform (13) and a radially outer platform, where the active part of the vane (43), which has a surface (64) forming a convex surface, and a s...

A bench for magnetoscopically testing a tubular part (12), such as a turbine engine shaft, the bench comprising a tool (14) of elongate shape for inserting inside the part and carrying endoscopic means for ultraviolet illumination of the inside surface of the part and for observing any defects of the part, and index...

The invention relates to a turbine engine combustion chamber including at least one ignition sparkplug (11) carried by an outer casing and extending through guide means (14) carried by a wall (3) forming a body of revolution of the chamber, the guide means (14) comprising a tubular guide (16) having the sparkplug (1...

The present invention relates to a combustion chamber of a gas turbine engine including a wall, a well (172) secured to the wall, the well forming a recess for a spark plug (13) leading into the combustion chamber, a spark-plug guide (175) mounted on the well such as to be transversally mobile relative to the axis o...

Monitoring the measurement of a fuel flow rate fed to an airplane engine, the measurement being delivered by means of a mass flowmeter. According to the invention, it is evaluated whether at least the following conditions are satisfied: • the signal delivered by the flowmeter is less than a given value (el, 40) ; ...

The invention relates to a combustion chamber (1) for a turbine engine such as an airplane turboprop or turbojet, the combustion chamber has inner and outer annular walls (3, 4) forming bodies of revolution that are connected together by an annular chamber end wall (5). The inner wall (3) is constituted by a si...

A turbine engine comprising at least first and second successive annular rows of stationary vanes, such as for example an annular row of stationary vanes (112, 112") of a nozzle stage (110) and an annular row of casing arms (120) arranged downstream from the nozzle, the turbine engine being characterized in tha...

The invention relates to equipment for coating the airfoil of a turbine blade of a turbine engine in a coating block comprising a base (11) on which a molding block (12) is positioned for the flow of the coating metal said molding block comprising a cavity defining a reference plane on the block for positioning same...

The invention relates to an energy system using as fuel natural gas stored in liquid form in at least one tank (3) containing liquefied natural gas, the system comprising a feeder device (13) provided with a heater device (15) for heating liquefied natural gas (la) and/or natural gas vapor (lb), and making use of a ...

Assembly comprising a blade (20) and a platform on which the blade can be mounted, the platform surface having, between the leading edge and the trailing edge of the blade, a circumferential depression (40) the most hollow cross section (41) of which lies in the upstream half of the blade. The curve of the variation...

The invention relates to a sealing ring (60) intended to be pressed against a rotor disc of a turbine stage for an aircraft turbomachine the ring being equipped with a plurality of anti rotation pegs (66) for preventing it from rotating in relation to the rotor disc each peg (66) protruding axially from a ring body ...

The component elements of a jet engine combustion chamber are assembled together in a manner that is designed to facilitate maintenance while also improving aerodynamic performance. In an embodiment, the outer cap (16) and the inner cap (17) have tongues (24, 25) and the chamber end wall (14) has corresponding tongu...

The present invention relates to a variable-setting stator blade, housed in a turbomachine casing, comprising an aerofoil (12) , a plate and a pivot (14) , characterized in that it comprises a platform with a disc on one face fitted to the plate and on the other face pressing against the wall of the casing, the fitt...

The invention relates to a hollow blade having an internal cooling passage (24), an open cavity (30) situated at the free end (14) of the blade and defined by an end wall (26) extending over the entire end of the blade (14) and by a rim (28), and cooling channels (32) connecting said internal cooling passage (24) an...

Combustion chamber for a turbomachine, comprising a chamber endwall equipped with fuel injection means and axisymmetric walls connecting the chamber endwall to internal and external flanges for fastening to internal and external casings, these flanges including annular portions pierced by orifices of triangular or a...

The invention concerns a method for depositing a coating of a first metal alloy on a fibre (10) extending in main direction D comprising the following steps: (a) Providing a first mass (20) of a first metal alloy and heating the first mass (20) higher than the melting temperature of same so that said alloy is liquid...

The invention relates to a fiber structure (200) for reinforcing a composite material part woven into a single part by means of multilayer weaving between a first plurality of thread layers (C C) and a second plurality of thread layers (T T). The fiber structure includes a portion (204) having a decreasing thickness...

The invention relates to the field of injection elements (201) for injecting two propellants (E1 E2) into a combustion chamber especially designed for a rocket engine having at least one combustion chamber of the type comprising an injector combining at least one such injection elements (201). Such an injection elem...

The invention relates to a forging press of the hot-die type with an operating temperature above a temperature T, comprising two dies (7, 8) between two die support elements (4, 5), a thermal insulation means (6, 6') being placed between each die (7, 8) and its support element (4,5). The press is characterized in t...

THE INVENTION RELATES TO A METHOD FOR PRODUCING A FIBROUS PREFORM FOR THE MANUFACTURE OF A TURBOMACHINE BLADE MADE OF COMPOSITE MATERIAL THE METHOD INVOLVING USING THREE DIMENSIONAL WEAVING TO CREATE A FIBROUS ROUGH FORM (100) IN A SINGLE PIECE WITH LAYERS OF LONGITUDINAL THREADS (C TO C) JOINED TOGETHER BY THREADS ...

The invention relates to a fiber structure (S1) for reinforcing a composite material part said structure being woven into a single part by means of multilayer weaving between a first plurality of thread layers (t10,t20,t30) extending in a first direction and a second plurality of thread layers (10,20,30) extending i...

The invention relates to a fibrous preform (20) which is formed from a fiber structure woven by means of three dimensional weaving having a plurality of warp thread layers interconnected by woof threads from a plurality of woof thread layers. The fibrous preform has a first portion (12) and a second portion (14) whi...

The invention relates to a gasket device (10) for the bearing of a turbomachine that can separate an oil enclosure (5) and an air enclosure (6) of the turbomachine comprising a segmented gasket (7) for providing the main tightness of the device (10) and a supporting envelope (14) for holding the segmented gasket (7)...

The invention relates to a part comprising a coating over a métal substrate made of a superalloy, the coating including a métal sublayer covering said substrate, characterized in that said métal sublayer contains a nickel aluminide base and further contains 0.5 and 0.95 atomic % of one or more stabilizing éléments...

The invention relates to a Jacquard weaving loom (100) for creating a fabric by weaving between a plurality of warp threads (201) and a plurality of woof threads (202). The fabric includes a predetermined number warp threads per length unit and a predetermined number of warp thread layers. The loom includes a comber...

An annular wall of a combustion chamber (10) of a turbo engine comprising a cold side (16a 18a) and a hot side (16b 18b) a plurality of primary and dilution holes (30) distributed in a circumferential row to allow air circulating on the cold side (16a 18a) of the annular wall to penetrate into the hot side (16b 18b)...

The present invention relates to a method of repairing a one-piece bladed disc or blisk of turbomachine having at least one damaged zone, by build-up of metal in said damaged zone by means of a build-up welding machine, which comprises the steps of preparing the damaged zone, of building up the zone with metal and o...

The invention provides a mechanical part for hinging to other mechanical parts at its ends (lOa), the mechanical part being made at least in part out of composite material from a central fiber preform (13) and a peripheral fiber preform (11) both of three-dimensional woven fabric, which preforms are assembled togeth...

The invention relates to a turbine nozzle guide vane assembly comprising a plurality of vanes (12) made of composite material each vane comprising an inner platform (14) an outer platform (16) having on the outer side attachment tabs (162 164) and at least one blade section (18) extending between the inner and outer...

The process consists in manufacturing a one piece axisymmetric part by superposition around a rotating cylindrical mandrel (2) of at least two respectively inner (7) and outer (14) metal coated composite fibrous structures wound in first and second crossed directions on said mandrel and in arranging between the cros...

The invention relates to an impregnation mandrel (100) for the production of gas turbine casings made from composite material said mandrel comprising: an annular wall (102) in which the profile of the outer surface corresponds to that of the internal surface of the casing to be produced; two side plates (104) the pr...

aThe invention relates to a device (100) for holding a fibrous texture on an impregnation former of a winding machine comprising a support forming crossmember (102) each end of which is intended to be fixed to one of the end plates (26) of the former a central shoe carrier (110) mounted on the crossmember and fitt...

Annular combustion chamber (10) to be fitted on a turbomachine and comprising a chamber end wall (22), a plurality of air and fuel injection systems (32) circumferentially distributed around an axis (34) of the combustion chamber (10) and mounted on said chamber end wall (22), and, an air manifold (100) associated w...

The electric propulsion system comprises a first stationary plasma thruster (111A) comprising a single first cathode (140A) a first anode (125A) and a first gas distributor and a second stationary plasma thruster (111B) comprising a single second cathode (140B) a second anode (125B) and a second gas distributor (121...

The invention provides tooling for injection-molding a part (26), the tooling comprising two cavity blocks (4, 21) each having a cavity (5, 22) formed therein of a shape corresponding to the shape of the part (26) that is to be molded once the cavity blocks (4, 21) have been superposed, at least one of the cavi...

The invention relates to a tool for manufacturing a foundry core for producing a cooling circuit for a turbine engine blade, including a mould (40) for injecting a paste, which comprises cavities (42, 44) for a first portion and at least one other portion of the core, and means (50, 54) for supporting and/or fitting...

A fuel injection system for an annular combustion chamber of a turbomachine, the system comprising support means for supporting and centering a fuel injector head, and a bowl arranged downstream from the support means and including at its downstream end an annular collar that extends radially outwards and that is co...

The invention relates to the field of Hall effect thrusters and in particular to a thruster (1) the downstream end of the annular channel (2) of which has a variable cross section so as to be capable of varying the thrust and specific impulse.

An elbow bracket for cables or pipes, supported by the structure of an aeronautical device, is original in that a reinforcing rib (17) of the elbowed main plate (13) is not assembled with the latter by welding but by tightening following a twisting of end-pieces (23) traversing slots (22) of the main plate (13) and ...

A system for ventilating a downstream cavity -of an impeller of a centrifugal compressor in a turbomachine, this cavity being delimited by the downstream face of the impeller and by an annular end-piece of a diffuser and being ventilated by taking air from the outlet of the compressor, the system comprising at least...

Abstract : The invention relates to a sectorized nozzle guide vane assembly for a turbomachine tur bine, comprising two sectorized annular platfbrms, an internai one (62) and an external one, which are connected by radial blades (63), at least one of thèse platfbrms (62) comprising, in the vicinity of its upstr...

The dilution holes (39) in a shell ring (2,3) of a turbomachine combustion chamber are covered with platelets (40) which delimit chambers (49) around them on the interior face of the shell ring. Ventilation holes (45) passing through the platelet cause those portions of the shell ring surrounding the dilution holes ...

The invention relates to the field of testing methods and specifically to a method for technical testing of a device including at least one operational step corresponding to a stable value of at least one operational setting of the device and/or of a test bench for the device. Said operational step ends within a m...

An injection system for a turbomachine combustion chamber, the system comprising a fuel injection nozzle for vaporizing fuel in the combustion chamber and a mixer/deflector assembly coaxial with the injection nozzle and serving to mix fuel and oxidizer and to diffuse the mixture in the combustion chamber, sa...

A device for guiding pivoting of variable-pitch vanes in a turbomachine, each vane having a pivot formed by a cylindrical axial shank which is guided in a cylindrical chimney of the casing and in a cylindrical orifice of a stationary element which surrounds the outside of the casing and which is centered and...

The invention relates to a repair process of a metallic piece, in particular of a rotor or stator blade of a gas turbine motor comprising an anti-wear layer (93CC, 94CC) formed by loading by welding of an anti-wear material to a part of its surface and whereof said layer is partially machined, characte...

The cooled gas turbine vane of the invention comprises a cast part (11) and a longitudinal sleeve (14)- obtained by shaping metal sheet; the cast part (11) comprises a longitudinal body provided with a longitudinal cavity (16) having a first -opening (19) and a second opening (20) at the ends; the sleeve (14...

The invention relates to a hollow blade comprising an internal cooling passage (24), an open cavity (30) located at the tip (14) of the blade and bounded by an end wall (26) and a rim (28) and cooling channels (32) that connect the said internal cooling passage (24) to the outer face of the pressure wall (16...

The controlled hot flap shutter makes it possible to reduce wear on the friction surfaces of said flap shutter with the nozzle seal and improve the tightness at this point.The friction surface (24) of the controlled hotflap shutter is made of metal, as is the nozzle seal.In this way, they c...

A method of moving a virtual articulated object (10) in a virtual environment (13) in a succession of unit movements, the articulated object (10) comprising a set of articulated elements (11) connected together by a set of joints (12), the relative positions of the articulated elements (11) being defined by ...

The invention relates to the provision of sealing for bleeding air to the cabin, the air passing through a cavity delimited, on the one hand, by the external shell (6) of the compressor and an annular structure (7) connected to the shell, and, on the other hand, by the external casing (12) of the diffuser gr...

A method of moving a virtual articulated object (10) in a succession of individual movements in a virtual environment, the articulated object (10) being specified in said environment by a global position, a global orientation, and a plurality of joint angles defining the positions of a set of articulated ele...

The present invention pertains to an automated polishing process for semifinished mechanical parts in titanium or titanium alloy, using a machine with abrasive belt mounted on a tangential contact wheel driven in rotation at a determined speed and applied at a determined pressure, the wheel travelling with r...

The present invention relates to a forging die with marking means including on one face a half-imprint of a part to be forged such as blade of a turbine engine, characterized by the fact that it include on said face, a means forming a marking alone two directions relatively to which the position of said impr...

The present invention pertains to a turbo-jet engine comprising a fixed structure, a fan rotor (2) integral with a drive shaft (5) supported by a first bearing (6) and a second bearing (7). It is characterized in that it comprises means (28) forming axial retaining means for the fan rotor (2) and/or forming ...

ABSTRACT A TURBOMACHINE ROLLER BEARINGThe present invention relates to a turbo machine roller bearing (10) that supports a shaft (4) constituted by a trunnion of a shaft line of a high-pressure spool of a turbo machine to rotate relative to a stationary support (8) that is connected to a casing of the ...

A device for lubricating a component in an assembly of parts, the device comprising a lubricant distribution chamber arranged in the vicinity of the component, feed means (30) for feeding said chamber with lubricant, and means connecting the chamber to means for taking the lubricant to the component, the dev...

A turbine ring forming a rotor shroud, the ring being of the type constituted by a plurality of sectors (11) interconnected end to end with interposed sealing systems comprising tongues (27, 28, 29) extending between adjacent sectors, said tongues being housed in slots formed facing each other in adjacent ra...

The present invention relates to a device for axially holding a ring spacer sector (16) of a high-pressure turbine (2) of a turbo machine, said spacer sector (16) comprising: an upstream radial wall (15) provided with an outer upstream tongue (20) for being engaged in a corresponding upstream groove (22) of ...

A device for lubricating a component in a turbomachine, in particular a shaft bearing in a turbojet, the device comprising an annular support part defining a lubrication chamber around the component, an annular cover mounted in sealed manner on the part and including a lubricating oil inlet, and an annular channel...

The invention relates to the sealing of the cavity from which air is bled off to the cabin, which cavity is delimited, on the one hand, by the external shell (6) of the compressor and an annular structure (7) connected to the shell, and, on the other hand, by the external casing (12) of the diffuser grating ...

The invention relates to a turbine stage for a turbine engine including an impeller rotating inside a sectorised ring (54) made of a composite material supported by a housing (14) each ring sector including a downstream circumferential edge (52) held radially resting on an annular tab (56) which is radially inserted...

The invention relates to an aircraft engine annular shroud (40 100) characterized in that it comprises:  on its internal surface (41 110) a peripheral annular groove (42 101) able to accept a plurality of blade roots (46 104);  an insertion opening (43 102) for inserting the blade roots (46 104) into the annular gro...

The invention relates to a compressor blade defined at each of the points on its surface by a sweep angle and a dihedral angle, comprising: -a root, -a tip, the distance between the root and the tip, measured along an axis referred to as the radial axis, perpendicular to an axis of rotation of the compressor, being ...

The invention relates to a combustion chamber for a turbine engine including an annular bottom wall (18) provided with injection systems (20) each centred on a respective axis (24) and each having an upstream end forming a socket (26 ) intended for receiving a head of a fuel injector and an annular fairing (40 ) cov...

In order to improve the cooling of an annular wall (13) of a turbomachine combustion chamber provided with microperforations (53) and in particular the cooling of a region of the wall facing a wake (52) caused by an ignition plug deflector means (60 68) are proposed these being designed to deflect the air (34 ) bath...

The invention concerns a method and system for forecasting maintenance operations to be applied to an aircraft engine comprising a plurality of elements monitored by damage counters each damage counter being limited by a corresponding damage ceiling characterised in that it comprises:  processing means (7) suitable ...

The invention relates to a supporting system (101 102 103) for supporting at least one pipe. Said system includes a comb comprising a bar and parallel teeth that are perpendicular to the bar. A locking device (30) essentially consisting of a pin is used to prevent a pipe passing between two of the teeth from moving ...

A method of designing a multistage turbine for a turbomachine in which each turbine stage comprises a stator row and a rotor row each made up of an annular row of airfoils, the method being characterized in that, for all of the stator or rotor rows, it consists in simultaneously modifying (36) the shapes of the airf...

Method for manufacturing a component using additive manufacturing, notably by nising or sintering particles of powder using a high-energy beam. According to the invention, this method comprises the following steps: provision of a digital mo del of a component that is to be manufactured, orientation of the model with...

The invention relates to a fuel injector (10) such as an injector for an annular combustion chamber of a turbomachine comprising a downstream head (16) having a central outlet (22) and an annular peripheral outlet (24) surrounding the central outlet (22) and an injector arm (12) upstream of the head (16) comprising ...

The invention relates to a device (100; 500) for inspecting the surface of an electrically conductive part, including a plurality of Eddy current probes (330, 331, 332...) arranged on a convex surface of the device, and means for applying the probes against the surface to be inspected into which the device is insert...