Snecma

Snecma Moteurs

Safran Aircraft Engines

Jacques Rene Bart

Stephane Rousselin

Didier Rene Andre Escure

Didier Rene Escure

Bruno Albert Beutin

Claude Marcel Mons

Antoine Jean-Philippe Beaujard

Yann Lebret

Jean-Luc Soupizon

Serge Rene Morreale

Gerard Philippe Gauthier

Philippe Pierre Bouiller

Laurent Donatien Behaghel

Jacky Raphael Michel Derenes

Patrick Charles Georges Morel

Patrick Morel

Stéphane Rousselin

Fabienne Lacorre

Cedric Magret

Nadege Hugon

Didier Escure

Amandine Roche

Emmanuel Patsouris

Laurent Michel Andre Berbiguier

Vanessa Le Rousseau

Patrick Charles Morel

Ornella Gastineau

Jacky Raphael Derenes

Cedric Kevin Magret

Laurent Michel Berbiguier

Didier René André Escure

Cédric Kevin Magret

A variable pitch rectifier for a compressor includes a plurality of radial vanes having respectively, at outer and inner ends of same, outer and inner pivots, the inner pivots being received between two upstream and downstream inner rings, which are assembled by a link device. The link device includes only a set of angular sectors of elastically deformable stirrups, arranged to grip together the inner peripheral edges of the upstream and downstream rings by clamping one against the other.

Variable pitch rectifier for a turbomachine compressor comprising two inner rings

A gas turbine engine for propulsion of an aircraft, the engine extending axially from upstream to downstream and including a composite part, a metal part, and a device for flexible fixing of the parts, the fixing device including: a flexible connecting element including a first fixing portion connected to the metal part by an axial connection and a second fixing portion connected to the composite part by an axial connection, the connecting element including an axially extending free end; and a rigid locking element including a fixing portion connected to the metal part by an axial connection and an axially extending free end, the free end of the locking element being aligned radially with the free end of the connecting element to limit deformation of the connecting element while the engine is in operation.

Gas turbine engine comprising a composite component and a metal component which are connected by a flexible fixing device

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

A device for locking a root of a rotor blade in a groove in a rotor disk of a turbomachine including: a circular ring sector configured to be mounted, transversely to the axis of the turbomachine, in a groove in the rotor disk; at least one locking wedge, which is rigidly secured and perpendicular to the ring sector, and extends parallel to the axis of the ring sector so as to hold the root of the blade radially in the groove; and at least one locking tooth extending from the ring sector radially with respect to the axis of the ring sector, so as to prevent the root of the blade from moving axially in the groove.

Device for locking a root of a rotor blade

A rotor of a turbomachine including a spinner which is attached removably to the upstream end of the rotor by an attachment system is provided. The attachment includes a dog clutch and a rotation-proofing system preventing the spinner from rotating with respect to the rotor.

System for attaching a turbojet engine spinner

A coupling device for coupling a turbine upstream guide vane which is coupled to a supporting part which itself attached to a stabilizing part is disclosed. The coupling device includes a interlocking device for interlocking a supporting end of the supporting part with a stabilizing end of the stabilizing part, and a retaining part to keep the supporting end and the stabilizing end interlocked. The coupling device may be used to couple an upstream guide vane of a turbojet turbine.

Coupling device for a turbine upstream guide vane, a turbine comprising same, and aircraft engine fitted therewith

A device for detecting breakage of a turbomachine shaft is disclosed. The device includes a shaft having an upstream end and a downstream end; a rod having an upstream end and a downstream end, and placed coaxially inside the shaft, the downstream end of the rod being securely fastened to the downstream end of the shaft and the upstream end of the rod being free to rotate relative to the upstream and of the shaft; and a sensor suitable for detecting a difference in speed of rotation between the upstream end of the rod and the upstream end of the shaft.

Device for detecting breakage of a turbomachine shaft

A device for, in a gas turbine engine, braking a turbine including a rotor driving a shaft capable of rotating with respect to a stator in the event of said shaft breaking is disclosed. The device includes a first braking member provided with at least one abrasive element and a second braking member including a ring-shaped element (A) made of a material capable of being eroded by the abrasive element. One of the two braking members being secured to the rotor and the other of the two braking members being secured to the stator. The braking members come into contact with one another through axial displacement of the rotor once the shaft has broken. The abrasive element of the first braking member eroding the ring-shaped element of the second braking member.

System providing braking in a gas turbine engine in the event of the turbine shaft breaking

A device for supplying ventilation air to a turbine rotor of a gas turbine engine including a first turbine disk, a second turbine disk, and a downstream shell ring together forming a one-piece drum is disclosed. The second turbine disk includes cavities machined in the rim to house the turbine blades, where the blades are axially retained by axial retaining segments. The downstream shell ring has at least one aperture drilled therethrough, downstream of the rim, which places an internal volume of the drum in fluid communication with at least one of the cavities via a passage formed in the segments.

Device for supplying ventilation air to the low pressure blades of a gas turbine engine

A device for, in a gas turbine engine, braking a turbine including a rotor, having at least one disk with a rim driving a shaft and capable of rotating with respect to a stator, is disclosed. The device is for the event of the shaft breaking and includes a first braking member, secured to the rim and provided with at least one cutting element, and a second braking member secured to the stator downstream of the rim and including a ring-shaped element made of a material that can be cut by the cutting element. The two braking members coming into contact with one another through axial displacement of the rotor once the shaft has broken. The cutting element of the first braking member cuts the ring-shaped element of the second braking member.

System for dissipating energy in the event of a turbine shaft breaking in a gas turbine engine

A device () for limiting overspeed in a turbomachine in the event of breakage of the turbine shaft (), comprising means () of propelling a pin () into the path of the blades (), these propelling means being controlled by means () that detect overspeed or that the turbine shaft has broken.

Device for limiting turbine overspeed in a turbomachine

The invention relates to a deoiling device. It comprises a tube (), a first bearing () and a second bearing (), the first and second bearings being placed in an oil chamber () in which an oil fog is maintained by rotation of the bearings. A deoiler () is provided in one wall of the oil chamber. The deoiler centrifuges oil in suspension in air and allows a deoiled air flow to pass inside the tube. The tube () comprises a closing cap () fitted with one or several outlet orifices () in its upper part designed to evacuate air, and an oil drain orifice () in its lower part.

Deoiling device and turbomachine comprising this device

A turbine module for a gas turbine engine includes at least an annular distributor and a turbine rotor inside a casing, where the annular distributor includes a plurality of elements in the form of a ring sector, of which a first part supports fixed blades positioned radially towards the turbine axis, and a second part forms a seal with the tips of the turbine rotor blades. The elements in the form of a ring sector are held inside the casing by attachment resources.

Turbine module for a gas-turbine engine

A jet engine with a system for recovering oil around the lubricating chamber of the rear rolling bearing of the shaft of the jet engine. The shaft is supported by a rolling bearing situated in a lubricating chamber surrounded by a single recovery chamber having a seal situated downstream from the rotor of the turbine driving the shaft.

Sealing system for the rear lubricating chamber of a jet engine

The device for rotationally locking a clamping nut for a component on an end of a hollow shaft, said clamping nut being screwed inside said shaft and having a free end, comprising: at least one shaft cutout on the radially inner periphery of said end of the shaft, at least one nut cutout on the radially outer periphery of an end of said clamping nut, and a locking plug intended to be placed in a locking hole formed by bringing a shaft cutout into coincidence with a nut cutout.

Device for rotationally locking a clamping nut for a component on a shaft, clamping nut and shaft comprising it, and aircraft engine equipped therewith

Growing community of inventors

Soisy Sur Seine, France

Jacques Rene Bart