Safran Aircraft Engines

Snecma

Hispano Suiza

Safran Transmission Systems

Bellal Waissi

Philippe Vertenoeuil

Alain Pierre Garassino

Sébastien Christophe Chalaud

Thomas Chauveau

Michel Gilbert Roland Brault

Pierre Charles Mouton

Jacky Novi Mardjono

Georges Jean Xavier Riou

Stéphane Prunera-Usach

Clément Dupays

Jordane Peltier

Gilles Le Gouellec

Lancelot Guillou

Jérémy Edmond Fert

Mathieu Jean Jacques Santin

Nuria Llamas Castro

Frédéric Paul Eichstadt

Lambert Olivier Marie Demoulin

Michel Gilbert Brault

Claude Sensiau

Nicolas Maurice Hervé Aussedat

Antoine Laigle

Arnaud Joudareff

Benoît Jean Henri Gomanne

Frantz Armange

Guillaume Mathon-Margueritte

José Rodrigues

Sébastien Chalaud

Stephane Prunera-Usach

Jordanne Peltier

Sebastien Chalaud

Benoit Jean Gomanne

In order to fill a reservoir while avoiding laborious manual filling operations, there is added to the existing device, including a supply duct, a pump and a measuring probe, a stop valve designed to interrupt the filling as soon as the desired level has been reached, which is detected for example by an air intake which controls the closure of the valve. Two level indicators are added and make it possible to ascertain either that optimum filling has been achieved or that a malfunction is present in the system. Application to the systems for oil filling of aircraft engine reservoirs from another reservoir arranged within the aircraft, generally common to all the engines.

Device and method for filling an oil reservoir of an aircraft engine

Portion of a fluid drainage conduit for a turbomachine, comprising an upstream stretch, a downstream stretch fixed relative to the upstream stretch and a retention chamber onto which the upstream stretch opens. The retention chamber is capable of communicating with the downstream stretch through a first aperture and a second aperture. The drainage conduit portion comprises an obturator to obturate the second aperture. The first and second apertures are provided so that when the obturator obturates the second aperture, the retention chamber retains fluid by allowing a fluid overflow to flow from the upstream stretch to the downstream stretch through the first aperture, and when the obturator does not obturate the second aperture, the fluid can flow from the upstream stretch to the downstream stretch at least through the second aperture.

Portion of a fluid drainage conduit for a turbomachine

A heat exchange and noise reduction panel the panel for an aircraft comprising: an external surface intended to be swept by an airflow and from which fins extend along a first and a second main predetermined direction; cavities forming Helmholtz resonators, linked to the first ends of channels for the passage of air, the second ends of which communicate with said airflow, such that said channels form necks, referred to as Helmholtz resonators, extending substantially along the first direction; and at least one oil flow chamber extending between said external surface and said at least one cavity, and intended to discharge the thermal energy carried by the oil, wherein said channels are formed, at least in part, inside said fins.

Panel for heat exchange and improved noise reduction for a turbomachine

Bypass turbine engine, comprising a gas generator surrounded by a nacelle and connected to the latter by tubular arms, a primary flow duct within the gas generator being externally delimited by a first annular casing of the gas generator, and a bypass flow duct of a secondary flow around the gas generator being internally delimited by a second annular casing of the gas generator and externally by a third annular casing of the nacelle, the second and third casings being connected together by at least some of the tubular arms, characterized in that it comprises at least one lubricant tank located in the annular space that extends between the first and second casings, and lubricant supply means of the tank or of each tank that comprise at least one supply line extending from the or each tank to at least one filler opening located at the level of the third casing, passing within at least one of said arms connecting the second and third casings.

Turbomachine with double flow and its lubricant reservoir

A cartridge for a filtering device, includes a cylindrically arranged pleated cloth, the pleats being parallel to the generatrix of the cylinder, wherein the cylinder includes a non-pleated region which is to be placed across from a fuel inlet into the filtering device.

Fuel filter having high resistance to icing

The invention relates to a lubrication system for turbomachine. The hydromechanical cutoff device is configured to close when a rotation speed of a turbomachine shaft reduces and becomes lower than a first threshold, and wherein the hydromechanical cutoff device is configured to open when the rotation speed of the shaft increases and becomes higher than a second threshold higher than the first threshold.

Hydromechanical cutoff device with hysteresis for a turbomachine lubrification system

The invention relates to a butterfly valve () for bleeding a compressor for an aircraft turbine engine, the valve including a valve body (), a butterfly (), and a device () for controlling the angular position of the butterfly, the device () including a mobile actuation member () connected to the butterfly by a link (), the member () being subjected: to a first adjustable pressure force (F) applied by air from the compressor, the first force (F) returning the butterfly () to a closed position; and to a second mechanical force (F) returning the butterfly () to an open position, and coming from an aerodynamic torque (C) applied by the air to the butterfly (), of which the axis of rotation () is off-centre relative to the butterfly.

Butterfly valve for bleeding a compressor for an aircraft turbine engine

A system for supplying a turbine engine with fluid includes a first low-pressure pump, a downstream hydraulic resistance and a high-pressure volumetric pump located between the first low-pressure pump and the downstream hydraulic resistance. The downstream hydraulic resistance includes at least one element selected among a fluid proportioning unit, a filter, a flow meter, an exchanger, a cut-off valve and an injection system. The supply system includes a second low-pressure pump and a supply variator configured such as to vary the flow of fluid supplied to the second low-pressure pump, the second low-pressure pump and the supply variator being located parallel to the first low-pressure pump.

System for supplying a turbine engine with fluid having a low pressure pumping assembly comprising two pumps in parallel

A turbine engine includes two rotary shafts and a lubrication unit. The lubrication unit has at least one pump which a casing inside of which a rotor is mounted and driven by one of the rotary shafts. The pump casing is rotated by the other rotary shaft such that the actuation of the pump depends on the difference between rotational speeds of the shafts. The shafts are a drive shaft and a fan shaft, respectively, wherein the fan shaft is driven by the drive shaft by means of a reduction gear which is lubricated by the lubrication unit. The reduction gear is annular and the pump passes axially therethrough.

Turbine engine provided with a lubrication unit

A geared fuel pump (') operates to supply a determined flow but at low or zero pressure rise. It is planned to add gland packing () between support bearings () of the pinions (), or between some of them, to provide hydrodynamic lift for these bearings, by delimiting a closed cavity () to provide lift by a fluid with better viscosity properties instead of using the fluid itself that is pumped. Possible application to fuel pumps for aircraft engines, in which the pump (&#x2032;) is a high pressure pump associated with a low pressure pump.

Gear pump intended, in particular, as a high pressure fuel pump

A multi-body gas turbine engine, especially an aircraft engine, comprising at least one low-pressure rotating body, a high-pressure rotating body, and a starter designed to rotate the high-pressure body in order to start the engine, wherein the starter is coupled to the low-pressure body and the engine comprises a first disengageable coupling device disposed between the low-pressure body and the high-pressure body, for rotatably connecting the high-pressure body to the low-pressure body so as to allow the starting of the engine by means of the starter.

Gas turbine engine comprising a starter engaged with a low-pressure body

A gearbox to be mounted on a turbomachine and driven by a radial drive shaft of the latter. The gearbox has a three-dimensional or sinuous shape, which can house a large quantity of equipment to be driven, without occupying a large amount of space in any dimension, since the gearbox remains close to the turbomachine and the equipment can be distributed over a large surface. The drive train of gears successively extends into several non-parallel planes and comprises an axial branch on the turbomachine and a branch forming an arc of circle around the turbomachine.

Drive gearbox on a turbomachine, consisting of a drive train with gear lines extending into non-parallel planes

The tank for a turbine engine comprises a partition separating a first compartment from a second compartment of the tank , the partition having a first end and a second end, the second end being closer to the bottom of the tank than the first end, the partition being inclined from the first end to the second end in the first direction and in the direction of the first outlet to the second outlet , the partition comprising at least one first Through-hole near the first end and at least one second through-hole closer to the second end than the first hole.

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Bellal Waissi