Snecma

Safran Aircraft Engines

Societe Nationale D'etude Et De Construction De Moteurs D'aviation-snecma

Laurent Gille

Serge Rene Morreale

Gerard Philippe Gauthier

Ion Fintescu

Gilles Alain Charier

Serge René Morreale

Laurent Donatien Behaghel

Benjamin Philippe Pierre Pegouet

Jean-Yves Picart

Jean-Pierre Mourlan

Jean-Pierre Andre Joseph Mourlan

Matthieu Savarit

Gérard Philippe Gauthier

Benjamin Pegouet

An oil distribution device for a rotating planet carrier of a step-down gear of a turbomachine is configured to be fixedly joined to a tubular member for supporting a bearing of the planet carrier, said oil distribution device having an oil inlet and a row of oil outlets at the external periphery thereof, said oil distribution device having at least two internal cavities which are connected in series by at least one calibrated port, one of these cavities, referred to as the receiving cavity, being connected to said oil inlet, and internal calibrated channels for conveying oil which extend substantially radially from said cavities as far as ports of the periphery of the device in order to form said oil outlets.

Oil distribution device for a rotating planet carrier of a mechanical reduction gear of a turbomachine

A rotary planet carrier for a mechanical reduction gear of a turbomachine having an annular row of tubular members for supporting bearings that are parallel to one another and to an axis of rotation (X) of the planet carrier. The tubular members include grooves for oil to flow through that are connected to oil ducts that extend from the grooves to an external peripheral surface. The grooves are rectilinear and parallel to one another and to an axis of revolution (Y) of an internal cylindrical surface of a corresponding tubular member. Some of the grooves have a width about the axis of revolution that is greater than the diameter of the ducts connected to this groove. Some of the ducts are connected to the corresponding groove that is closest to the axis of rotation (X) of the planet carrier.

Rotary planet carrier for a mechanical reduction gear of a turbomachine

A turbine engine including at least one shaft and at least one bearing for rotatably guiding the shaft about an axis of the turbine engine, the bearing including a first radially inner ring and a second radially outer ring enclosing rolling members, wherein the first ring is floatingly mounted on the shaft via a fluid damping film.

Turbine engine comprising a floating bearing for guiding a shaft of the turbine engine

A compressor rotor for a turbomachine including at least two disks on a common axis carrying blades and connected together by a tubular wall, forming a surface of revolution, and a centripetal air bleed mechanism including air passages passing through the tubular wall, together with a wall extending along the tubular wall from the through passages up to one of the disks to channel the air stream inside the tubular wall.

Centripetal air bleed from a turbomachine compressor rotor

A pressure-balancing device for balancing pressure in at least one bearing enclosure of a turbojet, the enclosure including a mechanism feeding the bearing with lubricating liquid, an air intake, at least one sealing system placed between the stator and the rotor in front of and/or behind the bearing, a recovery mechanism recovering the lubricating liquid, and a removal mechanism removing the mixture of air and of traces of lubricating liquid towards a venting circuit. Downstream from the bearing enclosure and in the venting circuit, the balancing device includes a regulator system regulating the air removal flow rate, thereby enabling the flow rate to be variable as a function of the speed of the engine, to remain non-zero, and, at high speeds, to be lower than when the regulator system is not included.

Method and a device for balancing pressure in a turbojet bearing enclosure

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 device for regulating the flow rate of air feeding a turbine ventilation cavity of a turbomachine turbine section is disclosed. The device includes at least one tubular duct opening into a take-off cavity and leading into a turbine ventilation cavity, the pressure inside the take-off cavity being higher than the pressure inside the turbine ventilation cavity; an air flow rate regulation valve disposed in the tubular duct, the valve being suitable for moving under the effect of the pressure difference between the take-off cavity and the turbine ventilation cavity; and a mechanical return device for holding the valve in a maximum closure position for the duct so long as the pressure difference between the take-off cavity and the turbine ventilation cavity remains below a predetermined threshold pressure.

Device for regulating the flow rate of air feeding a turbine ventilation cavity of a turbomachine turbine section

A dynamic sealing system between two coaxial rotary shafts respectively comprising an inner shaft and an outer shaft. Connected to the inner shaft, the system comprises a sectorized annular assembly of wipers that are movable under the effect of centrifugal force, and an annular receptacle for liquid arranged in the inside surface of the outer shaft.

Sealing system between two coaxial rotary shafts

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.

Growing community of inventors

Dammarie les Lys, France

Laurent Gille