Abstract: The invention relates to a housing for covering the ends of a row of rotor blades of an axial turbomachine compressor, the housing being provided with a sealing device between the blade tips and the housing. It comprises a shell segmented along its circumference, each segment being fixed to the housing by a series of elastomeric elements in a recess in the shape of a channel cut into the inner surface of the housing. In this way, in the event of misalignment of the rotor relative to the stator, the rotor blades coming into contact with sections of the shell will be able to move to compensate for this misalignment while reducing the frictional forces generated by contact between the blades and the shell. In the event of alignment being re-established the segments of the shell will be able to resume their initial position because of the elastic behaviour of the elements.

Abstract: A combined machine for pumping and separating into two distinct and purified phases a two-phase liquid/gas mixture or fluid, is provided. A first stage of the combined machine is equipped with an intake for the two-phase fluid, in which the two-phase fluid is sucked, pumped and partially separated into two distinct phases. One phase is mainly liquid and the other phase is mainly gaseous. A second stage of the combined machine includes two zones, which includes a first zone and a second zone. In the first zone, the mainly liquid phase extracted from the first stage is degassed. In the second zone, the mainly gaseous phase extracted from the first stage is dried. In a third stage of the combined machine, the degassed liquid is forced back and pressurized.

Abstract: A system for connecting two substantially tubular members, particularly ferrules of an axial compressor case, is disclosed. The system includes two flanges, where each flange has a proximal face and a distal face; securing members for clamping distal faces one against the other having 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 flange proximal faces.

Abstract: Use of the stator blade platforms for the deposition of a track of adjacent abradable material inside an external turbomachine shell is disclosed. The stator blades are attached to the shell so as to define an annular edge that is substantially continuous and the abradable material is deposited using this edge to delimit a boundary of the track of abradable material.

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: A system for connecting two ferrules in an axial compressor case is disclosed. Each of the ferrules includes a substantially annular flange with a proximal face adapted to be integral with the ferrule, and a distal face. The system further includes securing members for clamping distal faces of both flanges one against the other. The securing members include at least one pair of jaws provided for being connected by a set of tensile members, each of the jaws of the pair being provided for abutting against the proximal face of one of the flanges. At least one jaw of the pair further includes a portion, such as substantially radial shoulders, provided for forming a positive connection with complementary portions in both flanges for a transmission of circumferential stresses between both flanges.

Abstract: A system for connecting two ferrules of an axial compressor case. A ferrule includes a female flange, while the other ferrule includes a male flange. Both the female flange as well as the male flange are substantially annular and include 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 includes 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: The invention concerns a novel type of turbomachine. The stator of the turbomachine comprises a plurality of profiled members forming stiffeners arranged on the blade stage. The profiled members are distributed uniformly at periphery of the blade stage and individually between two consecutive blades. The stiffeners are 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 the internal ferrules to have a limited displacement during the normal functioning of the turbomachine. This makes it possible to reduce the axial sizing of the turbomachine, and consequently its mass.

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: 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: 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: A turbo-engine stator blading is disclosed. The turbo-engine stator blading includes a crown of fixed blades mounted on a ring. Each blade includes a platform and each blade is fastened to the ring. The ring includes a plurality of individual receptacles for the each of the platforms, the 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: 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 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.