Snecma

Safran Aircraft Engines

Hispano Suiza

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

Philippe Pierre Vincent Bouiller

Stephane Rousselin

Gilles Alain Marie Charier

Michel Gilbert Roland Brault

Gilles Alain Charier

Anthony Lorand

Antoine Jean-Philippe Beaujard

Daniel Georges Plona

Didier Rene Andre Escure

Jean-Pierre Ruis

Jackie Raymond Julien Prouteau

Eddy Stephane Joel Fontanel

Maxime Aurélien Rotenberg

Stéphane Rousselin

Giuliana Elisa Rossi

Julien Foll

Daniel Germain Alexis Kettler

Frédéric Patard

Frédéric François Jean-Yves Patard

Emmanuel Da Costa

Michel Francois Raymond Franchet

G&eacute;rard Ernest Andr&eacute; Jourdain

G&eacute;rard Marcel Fran&ccedil;ois Mandet

Christophe Caplain

Antony Lorand

The invention relates to a turbojet bearing housing including a fixed envelope traversed by a rotor, this envelope including a cylindrical end surrounding a seal ensuring the leak tightness of the cylindrical end of the envelope with the rotor, this envelope being equipped with a shell screwed onto the cylindrical end thereof, this shell including radial channels emerging opposite the seal while being arranged so that an air stream traversing the seal towards the housing mainly comes from these radial channels.

Shell for reducing overpressure in the vicinity of the upstream seal of a turbojet bearing housing

A turbine engine unit for lubricating a bearing holder. A turbine engine unit is provided, including an inter-turbine housing that includes a hub including a bearing holder, a ferrule extending around and at a distance from the hub, at least one arm extending radially between the hub and the ferrule, and at least one lead-through for lubricating the bearing holder. The lead-through includes a first pipe having an end portion that can be screwed onto the hub so as to place the first pipe in fluid communication with the bearing holder, an intermediate portion secured to the end portion placed inside the arm when the end portion is screwed onto the hub, and a clamping portion secured to the end portion and rotatable by a clamping tool. The turbine engine unit is characterized in that the clamping portion is located between the screwable end portion and the intermediate portion. A corresponding turbine engine unit assembly method is also provided.

Turbine engine unit for lubricating a bearing holder

A journal configured to be driven in rotation in a housing of a turbine engine, or for an aircraft, the journal including: a circumferential main body including plural ventilation openings configured to allow plural axial airflows to circulate from upstream to downstream in the turbine engine, two consecutive ventilation openings being connected by a connecting segment, and a circumferential ring for recovering a flow of lubrication oil, which ring is rigidly connected to the main body and is radially inside the ventilation openings, the circumferential ring including plural radial discharge openings for allowing plural radial flows of oil to be discharged towards the outside, each discharge opening being radially aligned with a connecting segment of the main body to allow each flow of oil to be discharged radially between the airflows.

Journal for a turbine engine comprising a ring for recovering a flow of lubricating oil with a plurality of lubricating oil discharge ports

A venting pipe used to guide a gas stream in a turbojet including at least one hollow rotary shaft inside which the pipe is mounted, the pipe extending generally along an axis. The pipe includes at least two pipe segments configured to be aligned longitudinally and assembled to one another while retaining a degree of freedom in relative translation thereof, at least one of the segments including a deformable mechanism configured to deform radially as the pipe segments are tightened against one another in the shaft of the turbojet, to bear on the shaft. The pipe structure facilitates mounting of the pipe.

Turbojet venting pipe, method for mounting one such pipe and turbojet provided with one such pipe

A fan portion of a dual flow turbojet engine including a plurality of fan blades, a disk supporting the blades and configured to be rotated relative to a stator portion of the fan, along a longitudinal axis of the fan, and a system for setting the angle of attack associated with each fan blade, the systems configured such that the angle of attack of each blade varies according to a same setting law according to the angular position of the blade relative to the stator portion, along the longitudinal axis, the same setting law being periodic with a period of P=360&#xb0;/n, where n is an integer at least equal to 1.

Gas turbine engine having fan blades of adjustable pitch with cyclic setting

A turbomachine such as an aircraft turbojet including an electrical generator/starter that can be mounted and dismounted by axial translation in an upstream enclosure of the turbomachine between the low-pressure compressor and the high-pressure compressor, and couple to electrical cables which extend inside the structural arms of the intermediate casing of the turbomachine.

Turbomachine with integral generator/starter

A device for ventilating turbine components in a gas turbine engine which includes first and second turbine rotors mechanically independent of each other, the first turbine rotor includes an HP turbine disk and the second turbine rotor includes an LP turbine disk and with a first circuit for ventilating the LP turbine is disclosed. The device includes an air compression wheel arranged downstream of the HP turbine disk between the HP turbine disk and LP turbine disk in order to assist the circulation of the air in the first circuit.

Device for ventilating turbine disks in a gas turbine engine

Turbomachine such as an aircraft turbojet comprising an electrical generator/starter () that can be mounted and dismounted by axial translation in an upstream enclosure () of the turbomachine between the low-pressure compressor and the high-pressure compressor, and couple to electrical cables () which extend inside the structural arms () of the intermediate casing () of the turbomachine.

Swivelling nozzle for an aircraft engine, the nozzlebeing pivotally mounted about a transverse yaw axis by means of two elastically deformable one-piece articulationsmounted on two external pivotsof the nozzle and housed in engine case elements, the nozzle being caused to pivot by an actuatormounted on the engine case and connected by a linkto a pivotof the nozzle.

Swivelling exhaust nozzle for an aircraft engine

An assembly arrangement between an inner race of a bearing and a journal supported in rotation in this bearing includes a journal annular groove and a race annular groove which interact to form an annular channel when they are placed opposite one another. The assembly further includes a retaining ring placed in the annular channel, which prevents a relative movement in translation between the journal and the inner race. The assembly also includes at least one recess of the journal and at least one tooth of the inner race, which interact to prevent a relative movement in rotation between the journal and the inner race.

Assembly arrangement between a bearing inner race and a journal, race and journal suitable for such an arrangement, and turbomachine fitted therewith

A compressor with a centripetal air takeoff system that includes pipes installed between an outer collar and an inner collar. Each pipe is fitted in a hole in the outer collar and in a hole in the inner collar. The system further includes a locking mechanism between the pipe and the inner collar.

Compressor with centripetal air takeoff

An axially symmetric turbojet-engine exhaust nozzle which is directable as a unit. The exhaust nozzle is situated downstream of an exhaust duct (,) fitted with a spherical wall (,). A single control ring (,) driven by linear actuators (,) allows regulation of the nozzle cross section and direction. Converging flaps (,) are guided on an upstream side by the spherical wall (,) and are supported at a downstream side by a control lever (,) which hinges on the control ring (,) and rests upstream on an external surface (,) of the spherical wall (,). Diverging flaps (,) hinge on the converging flaps (,) to form an inner ring of hot flaps. The diverging flaps (,) are situated downstream in an extension of the converging flaps (,) and further hinge on an outer ring of cold flaps (,), which in turn hinge on the control ring (,). A synchronizing system connects upstream ends of the control levers (,) to the control ring (,) and ensures self-centering of the control ring (,), the outer ring of cold flaps (,) and the inner ring of hot flaps relative to the spherical wall (,).

Growing community of inventors

Samoreau, France

Philippe Pierre Vincent Bouiller