Abstract: The invention concerns a novel type of turbomachine. According to the invention, the stator of the turbomachine comprises a plurality P of profiled members forming stiffeners arranged on the blade stage while being distributed uniformly at its periphery and individually between two consecutive blades, the stiffeners being fixed to the internal and external ferrules of the stator in order to uniformly increase the axial and radial stiffness of the stator in normal operation of the turbomachine and to allow to the internal ferrules to have. The invention makes it possible to reduce the axial sizing of the turbomachine, and consequently its mass. Application to aircraft engines, such as jet engines.

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 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 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 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 straightener blade for a turbomachine, comprising a platform arranged at a radially external end of the blade and adapted to be engaged in a annular groove of a housing, and a threaded rod radially extending outwardly from the platform and adapted to pass through an orifice of the housing in order to receive a fixing nut, the upstream and downstream edges of the platform each comprising a protrusion extending in the plan of the platform in order to limit the rotation of the platform in the groove when the nut screwed on the threaded rod is tightened.

Abstract: This invention relates to a system for connecting two ferrules in an axial compressor case. Each of the ferrules comprises a substantially annular flange and comprising a proximal face adapted to be integral with the ferrule, and a distal face. The system further comprises securing members for clamping distal faces of both flanges one against the other. Said securing members comprise at least one pair of jaws provided for being connected by a set of tensile members, each of the jaws of said pair being provided for abutting against the proximal face of one of the flanges. At least one jaw of said pair further comprises means, such as substantially radial shoulders, provided for forming a positive connection with complementary means in both flanges for a transmission of circumferential stresses between both flanges.

Abstract: This invention relates to a system for connecting two ferrules of an axial compressor case. A ferrule comprises a female flange, while the other ferrule comprises a male flange. Both the female flange as well as the male flange are substantially annular and comprise a proximal face intended to be integral with the ferrule, and a distal face. The male flange is intended to be introduced into a space bound by an axial extension of the female flange. The system further comprises a trim intended to be introduced behind the male flange into the space and clamped between the proximal face of the male flange and a surface of the extension substantially opposite in order to space them apart and thus clamp the distal faces of both flanges one against the other.

Abstract: A system for connecting two substantially tubular members, in particular ferrules of an axial compressor case, comprising two flanges, each comprising a proximal face and a distal face and securing members for clamping distal faces one against the other comprising a junction latch adapted to be housed into at least one cavity and at least one collar having two side faces provided so as to abut against the proximal faces.

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 turbo-engine stator blading of the invention comprises a crown of fixed blades mounted on a ring, each blade comprising a platform intended to be fastened to the ring. The blading is characterized in that the ring comprises a plurality of individual receptacles for the platforms, the said receptacles being machined in the thickness of the ring, the form of each receptacle being complementary to that of the corresponding platform. By means of the receptacles, the mounting of the blades within the blading is both simple and accurate.

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 test rig of a machine (1) includes a distributed exploitation of the test results, where the signals originating from the sensors (2) are ordered into a single signal, passing through a broad pass-band cable (6), via a common acquisition module (5). The computers (11, 12, 13) in association with miscellaneous display means (7, 8, 9, 10) search for the measurements which interest them on pre-set frames of the signal by using lists of relations contained in a host computer (12).

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.