Abstract: The present invention relates to an overall monitoring method allowing to calculate the autonomy of a lubrication system of an airplane engine and also allowing the diagnosis and prognosis of a plurality of problems and breakdowns of the engine and of its lubrication system by means of measurements taken by sensors arranged in said lubrication system, the method comprising the step of calculating the status of the lubrication system at a given moment and calculating its evolution over time in order to determine the remaining lifetime before a breakdown.

Abstract: The present invention relates to a system for lubricating a turbomachine comprising at least one enclosure, called non-ventilated, with members to be lubricated and an air-oil mixture, said enclosure being closed and pressurized using dynamic pressure seals supplied with compressed air to create an airflow from the outside toward the inside of the enclosure, said enclosure comprising an outlet for conveying the air-oil mixture toward an air/oil separator, said separator being provided with an suction function favoring the flow of the air-oil mixture between the enclosure and the separator, characterized in that the lubrication system comprises additional suction means.

Abstract: The present invention relates to an automated method for manufacturing layer by layer a composite part with rotational symmetry and complex cross-section, comprising the following stages: a) a reel or roll comprising a reinforcement is continuously unwound; b) as an option, the reinforcement is impregnated with a liquid resin by passing through a bath; c) the impregnated reinforcement is wound onto a rotating cylindrical mandrel; d) the impregnated reinforcement is completely or partially polymerised in order to obtain a composite material; e) a support and/or support material is deposited on both sides of the composite material forming the part being manufactured in such a way as to fill the gaps surrounding said part.

Abstract: The present invention relates to a turbomachine comprising an air compressor (3) and a lubrication circuit with an oil tank (1), said oil tank (1) being possibly isolated from the rest of the lubrication circuit (4,4A; 6,6A) by means of an isolation valve (7), wherein the isolation valve (7) is configured so as to: operate, i.e. to close and open respectively as the engine (2) stops and starts; remain open when the engine (2) is running; remain closed when the engine (2) is stopped.

Abstract: The present invention relates to a method for manufacturing an air/fluid heat exchanger (1), said method comprising at least the following steps: a) on a first sheet metal plate (2), a plurality of tight folds are formed, said folds acting as fins (3), or, alternatively, the first sheet metal plate (2) comprising a first portion (2a) and a second portion (2b), tight folds (3) are formed only on the first portion (2a); said first sheet metal plate (2) or said first portion (2a) forming a sheet metal plate in the upper position; b) the tight folds (3) are opened on a portion across their height; c) the first sheet metal plate (2) obtained in step b) is placed on a second sheet metal plate (6), said second sheet metal plate (6) forming a sheet metal plate in the lower position, or, alternatively, the first portion (2a) obtained in step b) is folded on the second portion (2b), said second portion (2b) forming a sheet metal plate in the lower position, d) the tight portion of the folds (3) is brazed and the

Abstract: The present invention relates to a heat exchange system in a turbine engine comprising a number of units and equipment (10,20) to be cooled and/or lubricated, sais system comprising at least two distinct oil circuits (2,3) to cool and/or lubricate said equipment (10,20), characterized in that said system is configured to put said oil circuits (2,3) in thermal contact with each other on the one hand and with a fluid playing the part of a cold source on the other hand.

Abstract: The present invention relates to a method for calculating the oil consumption and autonomy associated with the lubrication system of an airplane engine during flights, preferably a turbine engine, on the basis of the measurement of the oil level in the tank of said lubrication system, allowing to manage the refills and maintenance and to detect either abnormal consumption or insufficient autonomy, characterised by at least one of the following methods: comparing different engines of the airplane and possibly a reference value, the engines used for said comparison being in more or less identical condition, in order to detect abnormal oil consumption; taking into account one or more interference effects that affect said oil level in the tank, these being linked at least to the thermal expansion in the tank, to the “gulping” and to the attitude and acceleration, in order to deduce the modification to the oil level due to a decrease in the total quantity of oil available as a result of said interference effect

Abstract: The present invention relates to an installation for lubricating and/or cooling in an aircraft engine comprising an oil tank (3), a main feed pipe (6) feeding a main pump (1) supplying a flow in a discharge line from the main pump (7) to one or several systems (2) to be lubricated and/or cooled, wherein the installation comprises a feed pipe for an auxiliary pump (8) fitted in parallel onto the main pipe (6) and connected to an auxiliary feed pump (1A), the latter supplying a flow in a discharge line from the auxiliary pump (8A) connected by a three-way circuit on the one hand to a non-return valve (4A) directed towards the main discharge line (7), and on the other hand to a hydraulically-operated (9) recirculation valve (5), in order to divert the flow from the auxiliary feed pump (1A) into a return line (8B) directly towards the tank (3).

Abstract: The present invention relates to a turbomachine comprising an air compressor (3) and a lubrication circuit with an oil tank (1), said oil tank (1) being possibly isolated from the rest of the lubrication circuit (4,4A; 6,6A) by means of an isolation valve (7), wherein the isolation valve (7) is configured so as to: operate, i.e. to close and open respectively as the engine (2) stops and starts; remain open when the engine (2) is running; remain closed when the engine (2) is stopped.

Abstract: A multifunctional shutting device for a lubrication filter includes a safety device with triple valve shutting. The safety device includes a first valve for closing the oil intake in the filter with a view to dismantle the filter, a second bypass valve that opens when the filter is blocked and a third valve that opens in the event of excess pressure in the hydraulic circuit. The multiple valve structure is particularly applicable to the lubrication system in an aircraft engine but can be used in other hydraulic circuits subject to similar issues.

Abstract: The present invention relates to a plug valve comprising a valve body and a shutter that can be actuated, in the form of a segment of a sphere provided with a mobile shaft in rotation and/or translation, said valve also comprising a double-barrier sealing system at the level of said shaft, said valve being characterised in that the joints of said double-barrier sealing system are maintained in place relative to the shaft by a single lid.

Abstract: This invention relates to a shutter device for the precision control of a flow, comprising at least one organ for shutting a section for the passage of a flow, the motion of which is proportional to that of an actuator controlling it, wherein said device comprises at least two shutter organs controlled by the actuator by means of a transmission allowing to obtain slightly different proportionality coefficients for the motion of said organs.

Abstract: This invention relates to a flap valve with a shutter and a pneumatic actuator that is integrated into the valve, said actuator comprising a metal bellow interdependent with the shutter, wherein said bellow is directly welded onto an intermediate flange downstream from the valve and directly onto the shutter at the level of an end part upstream from the valve. The invention also relates to the use of such a valve as an isolating stop valve in the aerospace sector, preferably at high or cryogenic temperatures.

Abstract: The present invention relates to a bearing for maintaining an inner mobile structural component with revolution symmetry, rotating inside an outer structural component, which is itself fixed or mobile, said bearing comprising a set of balls and at least one joining member which provides the mechanical contact between said balls and said outer structural component, said bearing also comprising a pressurized-oil damper known as a “squeeze film” damper, arranged at the annular contact surface between said joining member and the outer structural component, said bearing comprising at least two annular elastic seals, each arranged in a groove, at the edges of said annular contact surface, wherein the annular elastic seals are U-shaped lip seals, the hollow space of which is directed towards the “squeeze film”, or are E-type seals, the hollow spaces of which are directed towards the “squeeze film”, the leakproofing for each seal being ensured by the contact between said seal and t

Abstract: The present invention relates to a guide vane stage of a compressor comprising an outer ring and an inner ring, which are both concentric and preferably circular. The rings are connected to each other via a series of fixed vanes, and are characterized in that at least the inner ring is provided with holes or apertures which allows one of the ends of the vanes to pass through these holes or apertures. The vanes also have at their end a second aperture intended to allow the passage of a retaining and rigidifying component having an elastic function, in order to hold them in pairs.

Abstract: A process for collecting oxygen-enriched air during a phase of aerobic flight of a space launch for combustion inside at least one cryotechnic rocket engine is provided. The launch rocket comprises at least one turbofan. The turbofan comprises a high-pressure spool comprising a high pressure compressor, a combustion chamber, turbines, and a low-pressure spool surrounding the high-pressure spool. The spools comprise a blower for collecting the external fluid in the form of a main flow and a derived flow. The main flow follows compression, combustion and depressurization in the turbofan engine. The derived flow is separated into oxygen-enriched air and oxygen-depleted air. The oxygen-enriched air is stored for combustion in a rocket engine, while the oxygen-depleted air is ejected.

Abstract: The present invention is related to a bearing for maintaining an inner mobile structural component with a revolution symmetry, rotating inside an outer structural component, which is itself fixed or mobile, said bearing comprising a set of balls or rollers and at least an outer race which provides the mechanical contact between said balls or rollers and said outer structural component, said bearing also comprising a pressurized-oil damper known as a “squeeze film” damper, arranged at the annular contact surface between said outer race and the outer structural component, characterized in that each side surface of the outer race is in contact with a side seal having an annular form, said seals being securely fastened to the outer race by means of a series of anti-rotation fixing members.

Abstract: A guide vane stage of a compressor comprising an outer ring and an inner ring, both of which are concentric and preferably circular is provided. The rings are connected to each other via a series of fixed vanes, characterized in that at least one of the rings is provided with a series of holes or apertures which allow the vanes to pass through these holes or apertures. The fixed vanes also have, at at least one of their ends, an aperture to allow at least one locking element to pass through, making it possible to simultaneously securely fasten all the present in the guide vane stage, on the non-functional side of the ring. The end of the fixed vanes through which the locking element passes is buried in an elastomeric element.

Abstract: The present invention relates to an axisymmetric structural component, one of the ends of which is fitted with an inner circular flange for assembling, by bolting. The axisymmetric structural component with a second axisymmetric structural component. The flange comprises housings for receiving fixing elements such as bolts, pins or threaded rods. The housings are arranged on the circumference of the said flange at regular intervals. Each housing is, in longitudinal section (A—A) along a plane passing through the rotational axis of the component, T-shaped and consists of a first essentially cylindrical portion which is longitudinally open on the inner face (x) of the axisymmetric structural component and transversely open on the contact face (y) of the flange in the assembly. A second essentially semi-cylindrical portion is mounted on the flange which is also longitudinally open on the inner face (x) of the said structural component having an essentially D-shaped transverse section.