Snecma

Safran Aircraft Engines

Gerard Philippe Gauthier

Serge Rene Morreale

Laurent Gille

Gilles Alain Charier

Jacques Rene Bart

Dominik Igel

Wilfried Lionel Schweblen

Eddy Stephane Joel Fontanel

Thomas Julien Roland Earith

Nelson Dos Santos

Eddy Stéphane Joël Fontanel

Jean-Pierre Mourlan

Gilles Yves Aouizerate

Jean-Yves Picart

Matthieu Etienne Attali

Benjamin Boudsocq

Amandine Roche

Sébastien Gameiro

Sébastien Bourget

Pierrick Charlemagne

A turbine rotor for aircraft turbine engine includes a mobile disc supporting mobile blades, the mobile disc including a plurality of slots into which are inserted the roots of the mobile blades a passage being formed between the bottom of the slots and the roots of the mobile blades inserted into the slots. The rotor also includes a circulation channel configured to allow circulation of fluid, the circulation channel including the passage, and a calibration device configured to allow the flow of a first fluid flow rate in the circulation channel when the temperature within the channel is less than a predetermined temperature threshold value, and to change state so as to allow the flow of a second fluid flow rate, greater than the first flow rate, in the channel, when the temperature within the channel is greater than or equal to said predetermined threshold value.

Device for detecting cooling abnormalities for an aircraft turbine engine

The invention relates to a heat exchanger () for heat-exchange between a first fluid and a second fluid, comprising a membrane separating the two fluids and a heat-conductive element () in thermal contact with the membrane and with the first fluid, characterised in that said heat-conductive element () moves between an active position and an inactive position, such that the capacity of heat exchange with the first fluid is weaker in the inactive position than in the active position. The exchanger is applied, in particular, for the cooling of fluid in the secondary stream of a turbofan.

Heat exchanger and turbine engine comprising such an exchanger

A device for discharging oil from an oil chamber located in a downstream part of a gas turbine engine, the device including: a mechanism discharging at least part of the oil contained in the chamber to exterior of the engine; and a drive mechanism for driving the oil, which allows passage of an air flow that assists in driving the discharge of the oil to the exterior of the engine. The drive mechanism includes: a ventilation port in the downstream part of the engine, such that the oil passes through the ventilation port; and a guide element arranged such that, after the oil has passed through the ventilation port, the oil is directed towards a downstream bleed area of the low-pressure turbine. A turbomachine can include such an oil discharge device.

Oil discharge device and turbomachine comprising such a device

An accessory gear box configured to be mounted on a fan casing of a turbojet engine, including: an input shaft; a plurality of accessory drive shafts; and a compartment forming an interface with an accessory arranged on the housing of the accessory gear box at a site of the accessory, the interface compartment including an inlet and an outlet configured to allow air to circulate inside the compartment, to insulate the accessory gear box from heat generated by the accessories.

Ventilation of an accessory gear box, and turbojet engine comprising such a gear box

A sealing device for a chamber including at least one rotary member and at least one static member of a jet engine and can contain a lubricating oil droplet suspension. The sealing device includes at least one brush seal that includes juxtaposed strands and is set to ensure sealing between at least one rotary member and at least one stationary member, a mechanism to recover part of the oil suspended within the inner space of the chamber, and a mechanism to deliver the recovered oil. The delivery mechanism is set up to generate a flow of oil along the strands of the brush seal, the oil flow being oriented in the direction of the rotary member. The brush seal thus provides better resistance to coking.

Sealing device for jet engine oil chamber

The invention concerns a system for providing a seal between two volumes (V, V) delimited by a part (A) mounted to rotate about an axis (A) and a stator (), said system (S) including an annular brush seal () that comprises:

Sealing system with annular brush seal

A lubricating and cooling epicyclic stepdown gearing, for example in an aeroengine turbomachine, including a cylindrical casing mounted on a planet-carrier of the gearing and forming a centrifugal scoop surrounding stationary oil-delivery strips, the cylindrical casing including radial ducts feeding nozzles pointing towards zones where the planet gears mesh with outer ring(s) of the gearing.

Lubricating and cooling epicyclic stepdown gearing

A method and a system for lubricating a turbine engine including at least three separate housings each including at least one roller bearing. The method pressurizes the housings through seals, of which two main housings are pressurized at a pressure higher than that of a remaining secondary housing, lubricates a secondary roller bearing only by injecting an oil mist from at least one of the main housings, the oil mist being supplied by a pressure difference between the main housings and the secondary housing, recovers a remainder of the lubrication oil injected into the main housings to supply the same to an oil tank, and supplies the air/oil mixture from the secondary housing to an oil separator.

Method and system for lubricating a turbine engine

A de-oiler system for an aircraft engine including a casing defining a volume containing a rotary shaft and a mixture of air and oil for processing is disclosed. The system includes a hollow rotary axle; a de-oiler structure fastened to the hollow rotary axle and rotating together with the hollow rotary axle, the de-oiler structure having an inlet first face communicating with the volume and an outlet second face connected to a passage formed in the hollow rotary axle; and a transmission device between the hollow rotary axle and the rotary shaft for communicating to the hollow rotary axle a speed of rotation V about its axis in such a manner that the speed of rotation V is greater than a speed of rotation v of the rotary shaft.

De-oiler system for an aircraft engine

A method for treating an airflow, laden with oil, flowing in a tube communicating with a rolling bearing enclosure of a gas turbine engine, wherein the airflow is made to travel into a coking box associated with a heating mechanism, in which the air is heated to a sufficient temperature to coke the oil particles contained in the airflow. Preferably, the solid residues produced by the coking are collected in the coking box.

Method for treating oil waste in a gas turbine engine

The turbojet has a bearing which supports, in rotation and in thrust, a low-pressure compressor shaft of axis Z-Z of the engine. The bearing is lubricated with oil by means of two nozzles. A feed tube is fastened to the nose cone of the engine. This tube connects the low-pressure compressor shaft to the engine nose cone. A skin lines the wall of the engine nose cone, leaving a passage for the circulation of oil. A plurality of radial oil return tubes are placed between the most eccentric part of the skin relative to the Z-Z axis and the bearing, for returning the oil to the bearing. The return of the oil into the bearing is located at a distance R from the Z-Z axis larger than the radius r of the feed tube.

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Champagne sur Seine, France

Gerard Philippe Gauthier