Abstract: A device for monitoring aircraft equipment is adapted to be arranged on said equipment and to measure and memorize at least one operation parameter of said equipment. The monitoring device is configured to be activated only in the presence of one or more parameters, representative of said equipment.

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 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 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 concerns a lubrication system in a closed circuit provided with a valve comprising a first position and a second position, as well as an IN inlet, a first BP outlet and a second M outlet, said IN inlet being connected to the outlet of the feed pump, the first BP outlet being connected to the bypass circuit and the second M outlet being connected to the feed circuit. In the first position of the valve, the flow entering via the IN inlet is diverted to the first BP outlet and in the second position, the incoming flow is diverted to the second M outlet, said valve switching from the first position to the second position and vice versa, when the incoming flow rate exceeds a predetermined threshold upwards and downwards respectively.

Abstract: The present invention relates to a combined machine for pumping and separating into two distinct and purified phases a two-phase liquid/gas mixture or fluid, preferably oil/air, entering the machine, comprising means for the suction, pumping and partial separation of the two-phase fluid, means for drying and extracting the separated gas and means for degassing and forcing back the separated liquid, comprising at least three physically separated stages (A,B,C) intended to be activated by a means that is internal or external to the machine, and built into a single casing: a first stage (A), 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 being mainly liquid and the other being mainly gaseous; a second stage (B), comprising two zones: a first zone in which the mainly liquid phase extracted from the first stage (A) is degassed, and a second zone in which the mainly gaseous phase extracted from the first

Abstract: A method and a system for lubricating a turbomachine including an oil tank, an oil feed pump, an oil/air separator, and at least two enclosures closed by air flow rate seals, each including a low outlet and housing shaft-supporting rolling bearings. The method injects oil from the tank into the enclosures by the pump to lubricate the bearings, introduces compressed air at a low flow rate into the enclosures via the seals to pressurize the enclosures, recuperates all of the air and the oil introduced into the enclosures via their low outlet, uses gravity and the pressurization of the enclosures to convey the oil/air mixture as recovered in this way to the oil/air separator, separates the oil and the air of the mixture by the oil/air separator, returns the oil to the tank, and exhausts the air to outside the turbomachine.

Abstract: The invention relates to an air-oil heat exchanger located at the inner shroud of the secondary duct of a turbojet. In characteristic manner, it comprises an oil circuit placed inside the separator nose and fins placed outside the top wall of the separator nose, between the leading edge of the separator nose and the outlet guide vanes.

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 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 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 process for lubricating an aircraft engine, and preferably a turboreactor engine, comprising at least one shaft (2), in which the pressurization of oil taken from a reservoir (3), the distribution of the oil via a downstream circuit (5) to elements (6) of said engine, and the return of the oil via an upstream circuit (7) to the reservoir (3) are ensured by means of a pump (1, 15, 17), the rotational speed of said pump (1, 15, 17) being variable and adjustable, characterized in that this rotational speed of said pump (1, 15, 17) is preferably regulated by a predetermined law in order to adapt to the actual lubrication needs of said engine.