Abstract: System for an aircraft, the system comprising: a turbine engine (2) with a hydraulic lubrication circuit (30); and a fuel cell (28) with a hydraulic circuit (40) for setting and maintaining the operating temperature of the fuel cell (28); wherein the hydraulic lubrication circuit (30) and the hydraulic circuit (40) form a single and common oil circuit and the oil circuit comprises a pump (50) with a heating element integrated in the pump for heating the oil. The pump may be an electric pump with an electric motor, wherein the electric motor comprises a coil fed with DC current forming a heating element for heating the oil. The pump may comprise a body and the heating element may be an electric resistor embedded into the body of the pump and in direct contact with the oil.

Abstract: An internal gear pump includes a pinion, a ring arranged around the pinion, and a cylindrical wall arranged around the ring. A support element, on which the pinion and the ring are supported, carries high-pressure liquid towards a recess located at the junction between the ring and the cylindrical wall, and also carries low-pressure liquid towards another recess located at another point of the junction between the ring and the cylindrical wall. The recess allows the load of the ring on the cylindrical wall to be reduced.

Abstract: System for an aircraft, the system comprising: a turbine engine (2) with a hydraulic lubrication circuit (30); and a fuel cell (28) with a hydraulic circuit (40) for setting and maintaining the operating temperature of the fuel cell (28); wherein the hydraulic lubrication circuit (30) and the hydraulic circuit (40) form a single and common oil circuit and the oil circuit comprises a pump (50) with a heating element integrated in the pump for heating the oil. The pump may be an electric pump with an electric motor, wherein the electric motor comprises a coil fed with DC current forming a heating element for heating the oil. The pump may comprise a body and the heating element may be an electric resistor embedded into the body of the pump and in direct contact with the oil.

Abstract: The present invention relates to a method for manufacturing a tank (1) comprising a main body (4) with several compartments (7), a base (6) closing the lower part of the main body (4), and a cover (5) closing the upper part of the main body (4), said method comprising the following steps: shaping sheets to produce the parts making up the tank (1); assembling each of the component parts by butt welding in order to produce the tank (1).

Abstract: An internal gear pump includes a pinion, a ring arranged around the pinion, and a cylindrical wall arranged around the ring. A support element, on which the pinion and the ring are supported, carries high-pressure liquid towards a recess located at the junction between the ring and the cylindrical wall, and also carries low-pressure liquid towards another recess located at another point of the junction between the ring and the cylindrical wall. The recess allows the load of the ring on the cylindrical wall to be reduced.

Abstract: A turbine engine reservoir has an oil deaerating device. The oil deaerating device includes a deaeration chamber for an air-oil mixture; an inlet of the air-oil mixture with a tangential inlet channel to form a vortex in the air-oil mixture contained in the chamber; and a vent for the discharge of air as a result of the deaeration of the air-oil mixture. The vent includes a rotor driven in rotation by the circulation of the air-oil mixture in the region of the inlet. The rotor filters the degassed air loaded with oil droplets in suspension. By centrifugal force, the rotor returns the collected oil onto the internal surface of the conduit of the vent. The collected oil drops back down into the chamber as a result of gravity.

Abstract: The present application relates to an anti-siphon valve for a tank including a body with an inlet, an outlet, and a passage for the fluid, the passage connecting the inlet to the outlet. The anti-siphon valve further includes a movable cut-off device interacting with a seat to close the passage. The cut-off device normally remains in the closed position and is designed to open the passage in the presence of a positive pressure difference between the inlet and the outlet. The anti-siphon valve further includes an auxiliary control mechanism for the cut-off device towards the passage opening, the control mechanism being designed to act on the cut-off device only to open the passage, so as to enable the cut-off device to move under the effect of pressure at the outlet independently of the mechanism.

Abstract: A circuit and a method for feeding oil to rolling bearings in a turbomachine is disclosed. The circuit includes an oil supply; an oil duct connecting the supply to lubrication enclosures, each enclosure containing at least one rolling bearing; an oil feed pump located between the supply and the lubrication enclosures; an oil recovery pump connected downstream from each lubrication enclosure; a pressurizing valve placed in the duct between the oil feed pump and the lubrication enclosures, the pressurizing valve being adapted to open when the pressure at its inlet exceeds a predetermined threshold pressure; a branch connection duct connecting the inlet of the pressurization valve to one of the lubrication enclosures in order to feed it with oil; and a feeding device which feeds the lubrication enclosures at a small oil flow rate so long as the pressure at the inlet of the pressurization valve has not reached the predetermined threshold.

Abstract: The present application relates to an anti-siphon valve for a tank including a body with an inlet, an outlet, and a passage for the fluid, the passage connecting the inlet to the outlet. The anti-siphon valve further includes a movable cut-off device interacting with a seat to close the passage. The cut-off device normally remains in the closed position and is designed to open the passage in the presence of a positive pressure difference between the inlet and the outlet. The anti-siphon valve further includes an auxiliary control mechanism for the cut-off device towards the passage opening, the control mechanism being designed to act on the cut-off device only to open the passage, so as to enable the cut-off device to move under the effect of pressure at the outlet independently of the mechanism.

Abstract: The invention relates to a gas flow separator dividing the flow into a primary and a secondary stream, especially for a dual rotor axial turbomachine. The separator comprises a splitter nose of the turbomachine and includes a generally wedge-shaped leading edge in the gas flow to be split. The flow separator also comprises a metal blade having a longitudinal section in the form of an “S” and located in the nose in contact with the back of the leading edge and extending from the leading edge to a rear end of the separator at some distance from the leading edge, so as to be in contact with a heat source, such as a heat exchanger, located at some distance from the leading edge.

Abstract: The present invention relates to a method for manufacturing a tank (1) comprising a main body (4) with several compartments (7), a base (6) closing the lower part of the main body (4), and a cover (5) closing the upper part of the main body (4), said method comprising the following steps: shaping sheets to produce the parts making up the tank (1); assembling each of the component parts by butt welding in order to produce the tank (1).

Abstract: The present application relates an oil feed system for a turbomachine having a tank designed to contain a volume of oil, a pump designed to suck the oil from the tank and discharge it to at least one device on the turbomachine, and an anti-siphon valve designed to prevent the flow of oil to the device or devices. The anti-siphon valve is located upstream of the pump and is designed to allow the flow of oil when the speed of the pump becomes higher than a speed R1. The present application also relates to a turbojet fitted with a fan and two anti-siphon valves designed to open at different rotational speeds of the first pump.

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 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 monitoring method that includes calculating the autonomy of a lubrication system of an airplane engine and also providing for 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 the lubrication system. The method further comprises 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 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, characterized 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 disclosure relates to lubrication systems for a jet aircraft engine. The system includes an oil tank with a high level sensor and a unit for monitoring the level of oil in a lubricating system. The monitoring unit includes a first input for a high oil level oil level signal, and a second input for a signal that the engine is running, and an output capable of generating an alarm signal. The monitoring unit is configured to generate an overfilling alarm signal, provided that the engine is running and the oil level is equal to or greater than the high level over a given period. This double condition avoids false positives, especially for engines subject to the phenomenon of “gulping”. For these engines the oil level in normal operation is significantly lower than when stopped. These measures can thus provide a reliable means of detecting overfilling.

Abstract: The invention relates to a gas flow separator dividing the flow into a primary and a secondary stream, especially for a dual rotor axial turbomachine. The separator comprises a splitter nose of the turbomachine and includes a generally wedge-shaped leading edge in the gas flow to be split. The flow separator also comprises a metal blade having a longitudinal section in the form of an “S” and located in the nose in contact with the back of the leading edge and extending from the leading edge to a rear end of the separator at some distance from the leading edge, so as to be in contact with a heat source, such as a heat exchanger, located at some distance from the leading edge.

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: The present invention relates to a surface air-cooled oil cooler (1) in an airplane engine comprising at least one first oil circuit (4) and at least a first (2) and a second (3) exchange surface positioned on either side of the first oil circuit (4) and each able to be swept by an air flow, said second exchange surface (3) being positioned in the cavity (9) provided with an air inlet (6) and an air outlet (7), said inlet (6) and/or said outlet (7) comprising covering means (8) that allow to regulate the air supply on the second exchange surface (3).