The invention relates to a Hall effect thruster (10) configured to be arranged inside or outside a spacecraft. The thruster has a concentrator (36) for collecting particles (P). The shape of this concentrator is defined by a continuous contour (C1) that wraps around the thrust axis and is such that along a major por...

The invention relates to a framework (10) for handling blades, comprising a bottom wall (12) carrying a plurality of intermeshed longitudinal (16a, 20a) and transverse (16b, 20b) partitions forming a grid (16, 20) defining a plurality of housings (22) each able to receive a blade (24). According to the invention, th...

The invention relates to an arrangement (200) for an aircraft turbine engine combustion chamber comprising an injection system and a fuel injector the injection system comprising a spray nozzle guide (26) the inner surface (40) of which delimits an opening (40 ) for centring the nozzle (82) which comprises an outer ...

The invention relates to a part coated with a protective coating (2) that forms a thermal barrier comprising a ceramic first layer (22). The protective coating also comprises a second layer (23) present on the first layer comprising predominantly by weight a first feldspar ore having a melting point greater than or ...

Device for lubricating a turbomachine rolling bearing (14) comprising a rolling bearing mounted between an internal component (21) and an external component the bearing comprising rolling elements (17) mounted between an outer ring (16) secured to the external component and an inner ring (15) secured to the internal...

The invention relates to the field of space propulsion, and more particularly electrical space propulsion. A space propulsion system (100) of the invention comprises at least: an electrostatic thruster(101) with at least a first electrical load; a resistojet (102); a propellant fluid feed circuit (104); and an el...

The invention relates to the field of turbomachine rotor blades and notably to a turbomachine rotor blade comprising a blade root and a blade tip which are separated by a blade height (h) and at least one intermediate portion (112a) having a negative tangential inclination and a distal portion (112b) situated betwee...

The invention relates to the field of casting and more particularly to a method for producing a ceramic core (1) for casting said core (1) having a shape that has at least one first lateral protrusion (11) the method involving at least a step of injecting a paste containing a ceramic granulate and a polymer binder i...

The invention relates to a stator (40) of an aircraft turbine engine comprising an annular row of stationary vanes (44) and an annular row of arms (48) characterised in that the trailing edges (42) of the stationary vanes are located substantially in a first transverse plane (P1) downstream from a second transverse ...

The invention relates to a method comprising the deposition of a coating consisting of a metallic material on the inner surface of the body (4) of the stator (36) the impregnation of said coating with a self lubricating composite material (20) the machining of inner cells (28) into the thickness of the coating (10) ...

The invention relates to a method for shaking out a sprue (30) of métal lost-pattern castings (32), the sprue of castings being fbrmed in a shell (1), in which at least one blade is moved by means of a machine without making contact with the sprue, so that the blade engages with the shell,breaks the latter into a pl...

The invention relates to the field of lost pattern casting and more specifically to a casting tree (1) for lost pattern casting and the method of assembly thereof. This casting tree (1) comprises at least one component support (8) at least one pattern (2) and at least a first male  female connection (9) connecting s...

An engine (10) for a spacecraft comprising a chemical thruster comprising a nozzle (30) for ejecting combustion gas, and a Hall-effect thruster. The engine is arranged such that the nozzle acts as an ejection channel for particles ejected by the Hall thruster when same is operating. The engine can deliver a high thr...

The invention relates to a turbine ring assembly including a plurality of ring sectors (10) forming a turbine ring (1), and a ring support structure (3) including an upstream ring-shaped flange (32) and a downstream ring-shaped flange (36), each ring sector (10) including a first horizontal sealing tab (21), an upst...

The invention relates to a method for manufacturing by selective powder bed fusion a blade preform for a turbine engine including a blade (2) and at least one detachable holder (6) attached to the blade the blade being manufactured in layers from a first edge (28) of the blade corresponding to a leading edge or a tr...

The invention relates to a method for manufacturing a shell mold for the production by lost wax casting of bladed elements (1) of an aircraft turbine engine including the following steps: a) creating an assembly (200) including a wax pattern (100) as well as a device for forming a cup for pouring metal (32b) and hav...

The invention concerns a method for determining the position of the cores in an injection mould, comprising the steps essentially consisting of: - selecting a core Rrep, from a population of cores, having the least deviation from the averages of the deviations measured between the k cores and the theoretical three-d...

Composition, characterized in that: - it comprises, in a solution of demineralized water: between 10 and 80, preferably between 15 and 20, more preferably 17, g/l of a composition of phosphoric acid H3PO4, and between 2 and 15, preferably between 4 and 8, more preferably 6, g/l of a composition of potassium permanga...

The invention concerns a device for assisting a propulsion system of a single engine helicopter comprising an engine linked to a power transmission unit (15) suitable for rotating a rotor of the helicopter characterised in that it comprises: a turbine (18) for driving the rotation of an output shaft (34) linked mech...

The present invention concerns a method for synchronising transmitted data frames having at least one maintenance algorithm executed by a maintenance computer of an aircraft said frames being transmitted on a first digital data link and at least second and third secondary digital data links comprising:  an initialis...

The invention relates to a method for deploying a satellite constellation which comprises: deploying by means of a single launcher a plurality of satellites (10) at an initial altitude above an initial orbit; piloting said satellites (20) such that each satellite reaches a drift altitude among a drift set in which t...

The invention concerns a tooling (24) for machining an annular groove of a turbomachine annular casing said tooling (24) comprising a machining tool (25) a base (33) first positioning means (28) for positioning the machining tool (25) relative to the base (33) along a first axis (Y) forming a radial axis second posi...

The invention relates to a method for producing a sealing component comprising a body (11) made of superalloy covered by a coating (13) to be placed in contact with a gas turbine blade tip (7). Steps are carried out in which: - a) the said new coating is produced by moulding from an alloy of the cobalt-nickel-chromi...

To improve air/fuel mixing at low speed the invention concerns an aerodynamic injection system (30) for a combustion chamber (8) of an aircraft turbine engine the system comprising a central body (70) comprising a first air circulation space (72) and a swirler (74) allowing air to penetrate into the first air circul...

The invention relates to a method for monitoring the wear of a turbomachine part the method comprising the steps in which by means of a computer: - a reference plane is provided; - by measurement of said part to be monitored a model is acquired of at least a portion of said part in the form of a three-dimensional mo...

The invention relates to an inlet body for a fluid injector for a turbomachine. The inlet body comprises a casing and an inlet nozzle (50) housed inside the casing and configured to serve as a seat for a mobile sealing member (20). The inlet nozzle (50) comprises a central duct (53) for the fluid and an annular rim ...

Method for regulating a supply circuit (10) comprising at least a first pump (12) and an upstream pipe (10a) leading to the first pump (12), the method comprising steps of: determining, in the upstream pipe (10a), the gas content of a flow being supplied to the first pump (12) and, when the value of the gas content ...

The invention relates to an assembly for a turbine engine comprising an oil circuit (24) including an air/oil heat exchanger (31), a primary bypass pipe (26) connecting an intake of the air/oil heat exchanger (31) to an outlet of the air/oil heat exchanger (31) and surrounding the air/oil heat exchanger (31) so as t...

The invention relates to a method for controlling the speed and the power of a turbine engine propeller, wherein at least two operating modes are implemented: - one operating mode, called "speed mode", in which the pitch (β) of the propeller is controlled as a function of the desired propeller speed, while the fuel ...

The invention relates to a method for assembling parts (A B) chosen respectively among a plurality of first parts and a plurality of second parts. The method comprises: - for each first part and each second part among the plurality of first parts and the plurality of second parts estimating (CST) a defectiveness ind...

The invention relates to a method for balancing a set of blades (5) intended to be arranged on a bare disc (7) of an aircraft engine, the bare disc (7) comprising a defined number of numbered cells (ai) intended to receive the same defined number of blades, which can have a spread of mass, said method comprising the...

The present invention relates to a cooling-fluid distribution element (150) intended to be fixed to a support structure to supply cooling fluid to a wall that is to be cooled, typically a turbine ring sector, facing it, the distribution element comprising a body defining an internal cooling-fluid-distribution volume...

An abradable structure (36) is provided, with regions (44, 45, 46) with lower resistance to wearing produced by labyrinth seal lips (4, 5), at specific points in the axial direction of the turbomachine, where lip interference could cause the rotor to block up, such as after a temporary shutdown of the turbomachine. ...

The invention relates to a housing (30) for managing access to an industrial network (10), to which industrial equipment (U1, U2, U3) is connected, the management housing (30) comprising: - a channel (30a) for access to an internet-type data network, said channel (30a) for access to the data network comprising a cut...

The invention concerns a method for extracting at least one foreign body lodged within a blade (110) of a high-pressure distributor of a turbojet engine, the high-pressure distributor comprising hollow fixed blades (110) between two annular shrouds forming a gas flow path, each blade being coated with a thermal barr...

The invention relates to a method for control of a cylinder (12), comprising the following steps: providing a cylinder that has a piston (22), a servo valve (14), and a measuring device (16) that comprises at least one first position sensor (28) and one second position sensor (30); taking position measurements (X1, ...

The invention relates to a method for monitoring the state of health of at least two vibration sensors of a twin-spool turbomachine comprising a low-pressure spool and a high-pressure spool, one vibration sensor being located at the front of the turbomachine, and another vibration sensor being located at the rear of...

The invention relates to a device for monitoring the lifetime of at least one hydraulic apparatus of an aircraft that is subject to variations in hydraulic pressure during flight, comprising an interface for receiving measurement data which are representative of hydraulic pressure (P). The invention is characterised...

The invention relates to a turbine shroud sector (2) made of ceramic matrix composite, of longitudinal axis X and which comprises a base (3) with a radially internal face (6), a radially external face (7) from which there extend upstream (4) and downstream (5) tabs for attachment to a shroud support structure, and a...

Disclosed is a method for repairing a composite material part (10), comprising: - producing a hollowed-out portion (30) by removing the composite material in a damaged area (20), - producing grooves (110, 120) extending on the two faces (11, 12) of the part (10) from the edges (32, 34) of the hollowed-out portion, -...

A method for electrical discharge drilling of a hole (18) in a part (16) made of electroconductive material, in particular for an aircraft turbomachine, the method using an electrical discharge machine comprising a head (12) that can move relative to the part and has a consumable EDM electrode (10), which is of elon...

Method for repairing a blade (10) of a turbomachine rotor, particularly a turbomachine fan, this blade comprising a vane (12) made from an organic-matrix composite and a metallic shield (14) bonded to a leading edge of the vane, the metallic shield (14) having a damaged region (20), the method comprising a step of r...

The invention relates to a tool for preforming a fibrous preform, comprising: - an inflatable first membrane (11) intended to accept the fibrous preform, - a second membrane (18) intended to attach to the first membrane (11) via a fixing system (20) in such a way as to form a fluidtight internal cavity (19) between ...

Method for controlling a first, a second and a third variable of a turbomachine as a function of a first, a second and a third turbomachine control quantity, each of which can become saturated as a function of the turbomachine operating parameters. The method comprises a first multi-variable correction (120) deliver...

The invention relates to a method for separating a first mechanical part (12) from a second mechanical part (14), wherein the second mechanical part (14) is bonded to the first mechanical part (12) by an adhesive film (16) along a connecting area, the first mechanical part (12) having a first specific thermal conduc...

The invention relates to a turbine ring assembly (2) extending about an axis (X-X), comprising a plurality of ring sectors (10) which are made from a ceramic matrix composite material and form a turbine ring (4) and a ring support structure (6) retained by a turbine housing (32), each ring sector (10) comprising a b...

The invention relates to a system and method for controlling an aircraft turbine engine. According to the invention, the control system (100) comprises: - a nominal-mode processing chain (110) comprising a global corrector (21) designed to control a speed of rotation of the turbine engine by delivering a position se...

The invention relates to a method for regulating a temperature of the exhaust gases of a turbomachine (1), the method comprising the following steps: - regulating the injection of fuel into a combustion chamber (5) of the turbomachine (1) such that the turbomachine (1) generates a target thrust; - regulating the inj...

An aircraft turbomachine rotor (2) comprising a rotor disc (20) extending transversely with respect to a longitudinal axis X, a plurality of blades (21) and a damping device (1) comprising: a support ring (7) configured to extend transversely with respect to the longitudinal axis X and configured to be mounted on th...

The present invention concerns a method for monitoring an actuating system of a movable component, in particular a movable component of a turbomachine such as a nozzle or a blade, the actuating system comprising a control device configured to deliver a position instruction to a first cylinder and a second cylinder, ...

The invention relates to an engine control device comprising a first control channel (V1) and a second control channel (V2), each control channel comprising a first sensor (CAV1, CAV2) and a second sensor (CBV2, CBV2), each configured to provide, respectively, a first measurement (A) and a second measurement (B) to ...

The invention relates to a method for measuring the speed of rotation of an aircraft engine shaft, comprising steps of: acquiring an alternating rotation speed detection signal across the terminals of a phonic wheel sensor, converting said alternating signal to a square wave signal, comparing a plurality of previous...

The invention relates to a method for controlling the fuel injection of a turbine engine using a fuel supply circuit (100). The supply circuit (100) comprises a pilot injection line (141) and a main injection line (142). During a transition of the supply distribution between the pilot injection line (141) and the ma...

The invention relates to a turbomachine moving blade (2) comprising at least one cooling circuit comprising at least one cavity (16; 16a, 16b) extending radially between the foot and the vertex, at least one air intake opening at a radial end of the cavity, a plurality of first discharge slots (18) arranged to open ...

The invention relates to a method for metering fuel in a fuel supply circuit of an aircraft engine, the circuit comprising a metering device for a fuel circuit of an aircraft engine comprising, downstream of a fuel pumping system and upstream of injectors: - a fuel inlet (E), - a metering device (FMV) and a cut-off ...

A blade for a turbomachine, extending longitudinally between a base and an apex, comprising a lower surface wall (16), an upper surface wall (17), a leading edge (14) and a trailing edge (15) and comprising a plurality of internal ventilation cavities (21, 22, 23, 27) which form a cooling circuit (20) of the blade, ...

The invention relates to a system (10) for evaluating a flow rate of a fluid from a tank (20, 21) comprising measuring means (17, 22, 23) for measuring a level of fluid in the tank (20, 21) and characterised in that it comprises means for estimating the flow rate of the fluid by means of an odourless Kalman filter s...

Cartridge for a filtering device said cartridge comprising a cylindrically arranged pleated cloth the pleats being parallel to the generatrix of the cylinder characterized in that the cylinder includes a non-pleated region which is to be placed across from a fuel inlet into the filtering device. ...

In order to test a semiconductor spark plug (10) a test method comprises a step consisting of depositing water on the head (16) of the spark plug between the two electrodes (18 20) of same so that the water forms a water meniscus (58) covering the semiconductor element (22) of the head a step consisting of applying ...

Method for creating at least one aircraft turbomachine vane using additive manufacturing, the method comprising a step of additive manufacturing of said vane on beds of powder using selective laser melting, the manufacturing being performed on a support plate (180) so that first or second circumferential edges are m...

A method for in situ deposition of a coating on a turbomachine casing by additive manufacturing, consisting in depositing a filament (100, 200, 300, 400, 500, 600) of an abradable material on an inner surface of said turbomachine casing (20A, 62) according to a predefined deposition trajectory in order to create a t...

The present invention relates to a fibrous structure (100) in the form of a band extending longitudinally (X) over a given length (L100) between a proximal part (110) and a distal part (120) and laterally (Y) over a given length (I100) between a first side edge (101) and a second side edge (102), said fibrous struct...

The invention relates to a propulsion assembly for an aircraft, comprising a motor and a propeller shaft (18) rotated by the motor, the propeller shaft passing through a sealed housing (16A) containing a lubricating fluid, as well as a bladed propeller coupled to the propeller shaft and comprising electrical devices...

Turbomachine ring and a turbomachine comprising such a ring and a method for repairing such a ring, the turbomachine ring comprising an essentially cylindrical support (31v) comprising a front surface (36) in which a notch (35) is made, one or more sectors (32) forming a crown configured to create an air stream sect...

The invention relates to a method for producing an ingot (2) consisting of a metal compound containing titanium, said method comprising the following steps: supplying fragments of raw material (3); melting the fragments of raw material (3) to form a liquid metal (4) in at least one basin; maintaining the liquid meta...

The invention relates to a device for guiding an element in an opening in a wall of a combustion chamber. Between the welds or solders (800) and the movement path (600a) of the rim of the ring (500), an intermediate space (881) is reserved in the groove (620) so that the welds or solders can protrude thereinto (at 7...

An injector nozzle (43) for a turbomachine comprises a primary fuel circuit ending in a fuel ejection pipe (66), and a secondary fuel circuit comprising an annular end portion for ejecting fuel (68) arranged around the fuel ejection pipe. A portion upstream from the primary fuel circuit comprises an annular channel ...

The invention relates to a mould (1) intended to be used for manufacturing a monocrystalline component by the pouring of metal and epitaxial growth, the mould comprising a cavity (10) in which the component is intended to be formed, and a housing (12) of elliptical cross section in which a monocrystalline seed (2) i...

The present invention relates to a method for detecting and locating a faulty measurement-acquisition channel in an acquisition system (10) comprising two redundant acquisition channels (A, B) for measuring a physical quantity in an environment, the method using a computing unit (20) comprising a memory (24) storing...

The invention relates to a tool (22) for removing a fan disc from a module of a turbine engine comprising a rotor and a stator, the rotor comprising the fan disc, a drum and a sealing part secured to one another via bolts each comprising a screw and a nut, each screw passing through a retaining member having at leas...

A system REG for regulating a physical parameter (y) of a real turbomachine system F(p) from a physical setpoint parameter (yc), the regulation system REG comprising a system OPTK for optimising the parameterisation gain K during the regulation, the optimisation system OPTK comprising a stability correction module (...

The invention relates to a method for producing a device for measuring deformations on a ceramic matrix composite part, and to the corresponding part. Said method for producing a device (3) for measuring deformations on a ceramic matrix composite part (1), in particular an aeronautical part, according to which an el...

The invention relates to a method (1, 28) for monitoring an engine control unit (2) having at least two separate paths (4, 6), each of the paths (4, 6) comprising at least: - means for carrying out a given application task AS, the application task AS consisting in part of a plurality of calculations which are perfor...

The invention relates to a confluence structure of an aircraft bypass turbine engine which comprises a confluence plate (13) with a downstream end (16) supported by a portion (20) that is movable in the direction of the axis (X) by a control mechanism (26 to 32) which can optionally be adjusted in flight. A mobile p...

The invention relates to a turbine (1) having a casing and a nozzle (2), comprising an outer metal shroud (9) rigidly connected to the casing, an inner metal shroud (5), and a plurality of CMC nozzle sectors (20) forming a ring extending between the outer metal shroud (9) and the inner metal shroud (5), each sector ...

A method for acquiring data for detecting damage to a bearing, comprising the following steps: (a) Obtaining (S10) a vibration signal from the bearing over a period of time; (b) determining (S14) spectrograms of said vibration signal at various instants of the period of time; (c) detecting (S22) the peaks on each sp...

Disclosed is a device for cooling a turbine (1) shroud, comprising: - at least one annular flange (33, 34) configured to be attached to an annular radial collar (32) of a shroud support structure (3), being arranged upstream of the turbine (1) shroud, relative to a direction of flow of an air stream, and comprising ...

The present invention relates to a holding system for the dismantling of a blade wheel, the blade wheel comprising: - a disc (2), - a plurality of blades configured to be mounted circumferentially around the disc (2), the plurality of blades defining a plurality of inter-blade spaces, the inter-blade spaces each bei...

A system (S) for supplying fuel (C) to the combustion chamber (5) in an aircraft turbine engine (6), comprising injectors (1) comprising a first pilot stage (10), a second pilot stage (16) and a main stage (13), the pilot stages (10, 16) being configured to supply a permanent flow of fuel (C), the main stage (13) be...

The invention relates to a jumper wire (6-A, 6-B, 6-C) for connecting an electrical cable (100-A, 100-B, 100-C) to a test device (2) with a view to diagnosing the state of health of the electrical cable (100-A, 100-B, 100-C), said jumper wire (6-A, 6-B, 6-C) comprising: an output port (7) configured to interact with...

A fuel distribution assembly (11) for a turbomachine, the distribution assembly (11) extending between a first interface plane (P1) and a second interface plane (P2) substantially parallel to the first interface plane (P1), the distribution assembly (11) comprising a plurality of distribution ducts (13), each duct (...

The present invention relates to a protection element (45.1, 45.2) for a compressor drum (20), which is intended to be arranged at least in part between a blade root (25) and the compressor drum (20), comprising: - a first lateral wall (51.1, 51.2) comprising an inner portion (54.1, 54.2) intended to cover an inner ...

The invention relates to manual deburring tool (1) comprising: a consumable carbide plate (10) having deburring edges (12) and a casing (20) which is configured to be grasped manually and has an internal cavity (22) for housing the plate the casing (20) comprising a body (25) and a cover (27) removably attache...

The invention relates to an upstream three-dimensional template (14) and to a downstream three-dimensional template (15) intended to be used within an outer turbojet casing (3), the inner surface (2) whereof is equipped with an abradable coating layer (7), upstream fastening means (12) for an upstream acoustic atten...

The invention relates to a method for adjusting a turbine engine part to be placed in a gas stream of the turbine engine, the part having previously undergone a material addition operation in order to fill in a defect in at least one area of the surface thereof, resulting in an extra thickness in at least one area o...

Blade for a turbomachine, comprising an airfoil part (12) and a blade root (11), the blade root (11) comprising at least one bearing surface (22) configured to cooperate with a fastening device (31) of the turbomachine (1), wherein at least the blade root (11) is made of TiAl, and wherein the bearing surface (22) is...

The invention relates to a method for detecting an anomaly in the operation of a component of an aircraft associated with at least one status indicator, the method comprising, for at least one acquired time sequence (Seq1, Seq2) comprising acquired values of said at least one indicator, steps of: - determining (E20)...

The invention relates to a metal powder for an additive manufacturing method, the metal powder comprising an alloy comprising, by weight, between 23% and 24.5% of chromium, between 9% and 11% of nickel, between 6.5% and 7.5% of tungsten, between 3% and 4% of tantalum, between 0.55% and 0.65% of carbon, between 0.3% ...

The invention relates to a metal powder for an additive manufacturing process, the metal powder comprising an alloy comprising by weight between 20% and 24% chromium, between 20% and 24% nickel, between 13.00% and 16.00% tungsten, between 0.02% and 0.12% lanthanum, between 0.05% and 0.15% carbon, between 0.20% and 0...

The invention relates to a digital system that makes it possible to determine at least one faulty component of an aircraft. The system comprises: - a first module (MDS1) for determining at least a first symptom (S1i) of the aircraft on the basis of state data (DEk) collected in the vicinity of the aircraft; - a seco...

The invention relates to an inner shroud sector (1) configured to internally delimit a secondary duct (41) of an aircraft turbomachine (50) the inner shroud sector (1) comprising a downstream end (2) which comprises an upstream longitudinal portion (3) and a downstream longitudinal portion (4) which are connected b...