Abstract: The invention relates to a device for measuring vibration amplitudes of the blade tips in a turbomachine, comprising a support mounted in an orifice of a casing of a turbomachine and wherein are housed two optical guides for the emission and reception of a light signal exiting inside the casing across from the tips of the blades of a turbine wheel. Each optical guide comprises an optical fibre connected by a mechanical connector to a needle of which the core is made of a material able to transmit a light signal and which is resistant to temperatures less than or equal to 1100° C. and which exits at its distal end in the casing across from the blade tips.

Abstract: The invention relates to the field of aerospace propulsion, and more particularly to a propulsion assembly having at least one channel defined by an inner wall and an outer wall, the channel presenting an inlet opening and an outlet opening, the assembly including a plurality of rocket engines oriented axially in the channel and forming ejectors for accelerating a flow of air in the channel to supersonic speed. Downstream from the outlet opening from the channel, the inner wall forms a single expansion ramp nozzle. The invention also provides an aerospace craft and a method of propulsion using such a propulsion assembly.

Abstract: An airplane having at least one turbojet and means for taking at least a portion of the boundary layer (30) of the flow of air over a surface of the airplane and for guiding the air that has been taken to an air inlet (54, 80) of the turbojet, the airplane being characterized in that the means for guiding air include means for diffusing the air that has been taken circumferentially in uniform manner over 360° at the air inlet of the turbojet.

Abstract: A metal annular casing (16) for a turbine engine compressor, the casing having at least one annular row of radial chimneys for receiving outer cylindrical pivots of variable-pitch vanes, together with an outer cylindrical centering track (28) that is continuous or interrupted and against which runners carried by an annular ring for controlling the pitch of the vanes are to come to bear, the casing being characterized in that the track is formed by blocks (30) of plastics material fitted onto the casing and that are fastened or held on the casing.

Abstract: According to the invention, the upstream rotor of a turbomachine, of longitudinal axis L-L, comprising a spinner (2) coaxial with the axis L-L and which is attached removably to the upstream end of the rotor (1) by attachment means, is characterized in that the said attachment means comprise a dog clutch (3, 9, 10) and rotation-proofing means preventing the spinner (2) from rotating with respect to the rotor (1).

Abstract: A method for bonding additional parts to a composite-material turbomachine part in a thermostatic oven includes a step of placing this composite-material turbomachine part equipped with the additional parts on a rigid support that cannot deform at the operating temperature and pressure and that is configured to espouse the desired final shape of the composite-material turbomachine part. The composite-material turbomachine part equipped with these additional parts is covered with a vacuum bag. The edges of this vacuum bag are sealed with respect to the non-deformable rigid support. A vacuum of determined pressure is applied to the vacuum bag. The determined operating pressure is applied to the vacuum bag in order to hold the composite-material turbomachine part equipped with these additional parts firmly against the non-deformable rigid support, the whole entity thus formed is heated to the operating temperature in the thermostatic oven for a determined time.

Abstract: The disclosure relates to an aircraft propulsion assembly including a nacelle having an intermediate housing and a front frame that is to be mounted downstream of an outer envelope of the intermediate housing. The front frame includes a deviation edge and an element forming a direct or indirect support for at least one flow deviation vanes, in particular, the deviation edge and the support-forming element are built into the outer envelope of the intermediate housing.

Abstract: A blade including a structure with aerodynamic profile including two opposite skins obtained by three-dimensional weaving of a fibrous reinforcement densified by a matrix, and a longeron including a fibrous reinforcement obtained by three-dimensional weaving and densified by a matrix, the longeron including a first part extending outside the structure with aerodynamic profile and designed to be connected to a drive hub in rotation of the blade and a second part arranged inside the structure with aerodynamic profile between the two skins. The second part of the longeron has a thickness substantially similar to that of the skins of the structure with aerodynamic profile. In addition, the fibrous reinforcement of the second part of the longeron has the same weaving armour as that of the reinforcement of the skins of the structure with aerodynamic profile.

Abstract: A method and a system for detecting the first signs of malfunction of an aircraft engine valve, including an acquisition device to acquire the output pressure measurements of the valve, and contextual and command data of the valve, a processor to define a set of indicators of the first signs of malfunction, according to the output pressure measurements and the contextual and command data. A set of estimators corresponding to the set of indicators of the first signs of a malfunction, is determined using a previously produced regression model. At least one distance between the set of indicators and the set of estimators is computed. The distance is compared to a threshold of the first signs of a malfunction, in order to detect the first signs of malfunction of the said valve.

Abstract: A reduction gear includes a sun pinion and planet pinions driven by the sun pinion and rolling on a fixed ring gear. The device includes an oil tank, an oil supply duct and oil routing ducts. The device also includes an oil ejection device at the end of the fixed supply duct, the orientation of which includes a radial component directed away from a common axis of rotation, and a cylindrical device for recovering the oil that can move in rotation about the common axis of rotation. The oil ejection device is linked by at least one duct to a lubrication device for the gear formed by the cooperation of the teeth of at least one planet pinion with an adjacent pinion. This device feeds the ducts which supply the oil to the parts to be lubricated, by virtue of the action of the centrifugal field.

Abstract: The resin that will fill a cavity for a part to be moulded and will be polymerised in it, does not reach the cavity until having circulated in a long conduit, formed on the parting line of the tool containing the cavity, so as to take advantage of the thermal inertia of the tool to heat the resin to the required stable temperature, instead of heating it in a less stable manner in the thermally insulated pipes external to the tool. Temperature variations resulting either from heat losses in the pipes external to the tool, or from overheating due to excessively fast polymerisation are thus avoided.

Abstract: A coupling made of composite material including a polymer matrix reinforced by a fiber structure is disclosed. The coupling includes a structural portion reinforced by a main fiber structure, and a first machining portion reinforced by a first fiber structure that is distinct from the main fiber structure. The matrices of the structural portion and of the first machining portion are identical. The first machining portion is situated on at least a fraction of the main face of the structural portion and is machined in a first machining surface. There is no intersection between the first machining surface and the fibers of the main fiber structure.

Abstract: A turbomachine compressor or turbine including annular anti-wear shims mounted against hooks of a stator, each shim being substantially of channel-section defining an annular groove for engaging on a hook, the shim mounted against the downstream hook bearing axially via its middle annular wall on the stator, or on the casing, and one of its side walls includes bearing means at its end remote from the middle annular wall for bearing against the casing or the stator, respectively, which bearing means are elastically deformable in an axial direction so as to urge the stator upstream.

Abstract: According to the invention, the method for defining the shape of a convergent-divergent nozzle of longitudinal axis L-L comprising a convergent part connected, at a throat, to a divergent part the downstream free end of which comprises scallops delimiting noise-reducing chevrons distributed in the circumferential direction, comprises defining beforehand the divergent part of the nozzle using a divergent first portion, a divergent second portion and a convergent portion, attributing an initial value to dimensional parameters defining the chevrons and the three portions, calculating performance criteria and checking that the calculated performance criteria satisfy predefined performance conditions.

Abstract: A method for measuring the deformation of a turbo-machine blade including: a step of positioning at least one accelerometer onto a local point of the turbo-machine blade; a first step of measuring the centrifugal force, by the accelerometer, at the local point of the turbo-machine blade along the given measurement direction at a first predetermined speed; a second step of measuring the centrifugal, at a second predetermined speed; a step of determining the angular displacement of the measurement direction of the accelerometer relative to the centrifugal direction as a function of the first acceleration measurement and the second acceleration measurement, said angular displacement corresponding to an angular deformation of the local point of the turbo-machine blade.

Abstract: The invention provides a fan casing for a gas turbine engine, the casing having a substantially cylindrical portion that terminates at one end in an annular flange made of composite material. The flange includes at least one setback in a fraction of its thickness and at least one bolt for fastening pieces of equipment passing right through the flange in the axial direction, the bolt for fastening pieces of equipment having a head that presents a flat that is to bear flat against a rim of the setback, and a shank forming a stud for fastening pieces of equipment on the casing.

Abstract: A link part for a turbine engine, in particular such as a turbojet, the link part being mounted between a fan cone and a fan disk supporting fan blades, the link part having an annular wall pierced by a plurality of orifices, each for receiving a fastener member and terminated by a substantially perpendicular rim having an outer surface that provides an aerodynamic extension of the fan between an outer surface of the fan cone and an outer surface of a fan blade platform, the annular wall being made of a first material that is composite and is provided on an inner surface of the rim with a ring made of a second material that is different from the first and that is suitable for radially retaining the fan blade platform.

Abstract: The invention relates to a method and a system for detecting an impact on an impeller wheel (7) of an aircraft engine, characterised in that it comprises: acquisition means (13) for acquiring a revolutions per minute of said engine and a series of deflection signals representative of the deflections on the blades of said impeller wheel at said revolutions per minute, and correlation means (15) for constructing signals for detecting impact on said impeller wheel by correlating each of the deflection signals with a predetermined signature of a shock on a blade at said revolutions per minute.

Abstract: The invention relates to a method for monitoring the operation of a fuel circuit shut-off valve comprising an LPSOV, a flow regulator, the shut-off valve, characterised in that it comprises: a step for ordering (30) the closure of the valves; a step for measuring (32) the fuel flow rate in the circuit qui carried out before the LPSOV is completely closed; and a diagnostic step (34) consisting of determining that said shut-off valve is defective if the fuel flow rate measured is not equal to zero and determining that said shut-off valve is operating correctly if the fuel flow rate measured is zero.

Abstract: An arrangement for the guiding of the flow of a liquid in relation to the rotor of a turbomachine, which includes an intermediary disc and a downstream disc of which the internal diameter and the axial position of the discs are defined in such a way that the tank is arranged inside the discs. The rotor supports a guide flange with an element of revolution of which the diameter of the section increases in the downstream direction, according to the direction of flow of the gases in the turbomachine. The downstream axial end of the flange is fixed to a portion of the rotor located downstream of the downstream disc and the upstream axial end of the flange is connected to the internal radial end of the intermediate disc.