Techspace Aero S.a.

Safran Aero Boosters Sa

Snecma

Techspace Aero

Albert Cornet

Nicolas Raimarckers

Bruno Servais

Denis Bajusz

Marc Strengnart

Jean-Louis Muller

David Depaepe

Stéphane Bougelet

Mathieu Pierre Chenoux

Jacques Charlier

Jean-Louis Jacquerie

Georges Broers

Yves Culot

Bernard Simeon

Marc Mon Fort

Francois Delamour

Jérôme Friedel

Nicolas Alain Bernard Potel

Nicholas Raimarckers

Antoine Stephany

Thomas Borlon

Olivier Descubes

Marc Montfort

Cédric Borbouse

Steve Houziaux

Geoffroy Ricardou

Sébastien Detry

Marc Monfort

Nicolas Raimackers

Mathieu Chenoux

System for an aircraft, the system comprising: a turbine engine () with a hydraulic lubrication circuit (); and a fuel cell () with a hydraulic circuit () for setting and maintaining the operating temperature of the fuel cell (); wherein the hydraulic lubrication circuit () and the hydraulic circuit () form a single and common oil circuit and the oil circuit comprises a pump () 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.

Hydraulic system

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.

Internal gear pump

The present invention relates to a method for manufacturing a tank () comprising a main body () with several compartments (), a base () closing the lower part of the main body (), and a cover () closing the upper part of the main body (), said method comprising the following steps:

Tank and method for manufacturing same

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.

Piston-controlled anti-siphon valve

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.

Circuit and a method for feeding oil to rolling bearings in a turbomachine

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.

Gas flow separator with a thermal bridge de-icer

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

Recirculation valve in an aircraft engine

The present invention relates to a method for manufacturing an air/fluid heat exchanger (), said method comprising at least the following steps:

Method for manufacturing a heat exchanger and exchanger obtained by the method

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.

Method for monitoring the oil system of a turbomachine

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:

Method for controlling the consumption and for detecting leaks in the lubrication system of a turbine engine

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.

Combined pumping and separating machine for the oil circuit of a turbojet

The present invention relates to a turbomachine comprising an air compressor () and a lubrication circuit with an oil tank (), said oil tank () being possibly isolated from the rest of the lubrication circuit (A;A) by means of an isolation valve (), wherein the isolation valve () is configured so as to:

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Verviers, Belgium

Albert Cornet