Snecma

Safran Aircraft Engines

Regis Eugene Henri Servant

Clement Cottet

Thierry Georges Paul Papin

Didier Gabriel Bertrand Desombre

Francois Marie Paul Marlin

Michel Gilbert Roland Brault

Laurent Jablonski

Stephane Rousselin

Gilles Alain Charier

Christophe Paul Jacquemard

Vincent Joudon

Christophe Marcel Lucien Perdrigeon

Son Le Hong

Serge Louis Antunes

Gael Bouchy

Philippe Verseux

Kaelig Merwen Orieux

Jean Pierre Galivel

Patrick Charles Georges Morel

Olivier Michael Molinari

Vivien Mickael Courtier

Emmanuel Houradou

Laurent Raberin

Frederic Jacques Eugene Goupil

Fabrice Cretin

Damien Lourit

Mathias Gautier

Christoph Marcel Lucien Perdrigeon

Brice Bruno Albert

Christian Largillier

Eric Nicolas Decerle

Julie Bellay

Noel Joseph Camille Robin

A propeller for an aircraft turbomachine, the propeller having; a hub extending around a first axis including openings distributed around the first axis, each of the openings having a substantially radial orientation relative to the first axis and extending through the hub, a system for controlling the angular setting of a blade which is mounted in each of the openings, and bearings for guiding the control system, which are mounted in each of the openings, the guide bearings including two guide bearings, one of which includes two annular rows of angular contact coaxial balls having different diameters.

Propeller for an aircraft turbomachine

The invention concerns an aircraft turbine engine (), comprising a gas generator comprising at least one annular gas flow duct (), the duct () being defined by two annular housings, respectively an external housing () and an internal housing (), extending one around the other and connected together by at least one tubular arm () for the passage of a lubricating oil line (). According to the invention, the line () comprises a first fixed section () secured to the external housing (), a second fixed section () secured to a piece of equipment () of the turbomachine capable of moving or vibrating during operation relative to the housings (), and an intermediate section () connecting the first and second sections (), this intermediate section () having a generally elongate shape and comprising longitudinal ends engaged and capable of swiveling and/or sliding in ends of the first and second sections ().

Aircraft turbine engine

An assembly comprising a propeller blade and its system for angularly adjusting the pitch of the blade including a bowl which is radially delimited by an annular wall extending about an axis for adjusting the pitch of the blade, the bowl having a bottom wall, a free lower end of the root being fitted axially into a complementary housing of the bottom wall in order to rotatably connect the bowl and the blade about the pitch-adjustment axis. The root of the blade comprises a first limiting face that engages with a first abutment face of the bowl to limit the rotation of the blade in the event of breakage of the lower end of the root.

Aircraft turbine engine comprising variable-pitch propeller blades

Device for distributing oil from a rolling bearing () for an aircraft turbine engine, comprising: —a rolling bearing (), —an oil distributor ring () and —an annular track () of a dynamic seal (), characterised in that it further comprises a nut () screwed on to a thread () of the distributor ring and bearing axially against an axial end of the inner ring so as to clamp it axially, and in that the annular track is configured to bear axially against the distributor ring and comprises rotating locking elements () engaging with the additional elements () of the nut.

Device for distributing oil from a rolling bearing for an aircraft turbine engine

Device for distributing oil from a rolling bearing () for an aircraft turbine engine, comprising: &#x2014;a rolling bearing (), &#x2014;a body () for distributing oil, which body is configured to be mounted on a turbine engine shaft (), said body comprising: i) a first outer cylindrical surface () for mounting the inner ring () of the bearing, ii) a ring-shaped scoop () for recovering oil, iii) a ring-shaped track () of a dynamic seal (), iv) a circuit () for lubricating the bearing and cooling the track, said circuit being formed in the body, characterised in that the ring-shaped scoop is the first scoop () which supplies a first portion () of the circuit with a view to cooling the track, and in that the body comprises a second ring-shaped scoop () for recovering oil, which scoop supplies a second portion () of the circuit with a view to lubricating the bearing.

The invention relates to a turbomachine module (), comprising: &#x2014;a rotating housing (-) supporting a propeller provided with a plurality of blades (), &#x2014;a system for varying the pitch of the propeller blades (), the system comprising a control means, and a mechanism for varying the pitch of the propeller blades, characterised in that the system is supported by the rotary housing (-), in that the control means comprise an annular row of rotary actuators (), and in that the mechanism for varying the pitch of the blades comprises a synchronisation ring () that is driven to rotate by rotary output shafts () of the actuators (), the synchronisation ring () being guided in rotation relative to the rotary housing (-) by guide means and meshed by a first toothing () with pinions () of the blades ().

Turbomachine module for a propeller having variable-pitch blades and turbomachine comprising same

The invention relates to a module of a turbomachine of longitudinal axis X, the module comprising: &#x22c5;&#x2014;a rotary casing () that rotates about the longitudinal axis and bears a propeller () which is provided with a plurality of blades (); &#x22c5;&#x2014;a fixed casing () comprising a cylindrical wall () extending between an inner wall () and an outer wall () of the rotary casing (); and, &#x22c5;&#x2014;a system () for changing the pitch of the blades of the propeller, mounted around the fixed casing and comprising: a control means () comprising a movable body () that is able to move axially on said fixed casing, at least one load transfer bearing () comprising an inner ring () that is connected to the movable body (), and an outer ring (); and a connection mechanism () for connecting the outer ring () to the blades of the propeller. According to the invention, the module further comprises a feathering device () for feathering the blades of the propeller, this device () comprising an annular row of springs () that are arranged around said fixed casing and extend axially, the springs () comprising first axial ends () that bear against a ferrule () of the fixed casing, and opposite second axial ends () that bear against said inner ring ().

Turbomachine module equipped with a system for changing the pitch of the blades of a propeller and with a device for feathering the blades

A unit including an intermediate turbojet casing formed by a hub including a downstream transverse endplate having formed therein at least one first opening putting the inside of the hub into communication with a duct extending downstream from the endplate and opening out at its downstream end via a second opening formed in an outer annular shroud extending downstream from the hub for defining the inside of an annular flow space for a secondary stream, is provided. The upstream end of the duct is fastened to the downstream endplate of the hub by releasable elastic engagement.

Turbojet with a discharge duct

A support structure suitable for interposing between the engine and the nacelle of an aeroengine and suitable for being fastened on an intermediate casing is provided. The structure includes a shroud having a plurality of sectors, a plurality of radial arms each installed between two adjacent shroud sectors, and a plurality of fasteners for fastening the plurality of shroud sectors to the plurality of radial arms. The shroud sectors and radial arms form a skeleton for transmitting structural forces within the intermediate casing. The structure includes non-structural fairings mounted on the skeleton and suitable for reconstituting the airflow passage. Each of the shroud sectors and radial arms is formed by a metal frame without mechanical discontinuity, each shroud sector metal frame defining at least one opening that is closed by a cover and each radial arm metal frame defining at least one orifice for receiving a closure plate.

Casing support structure

A turbojet engine including an intermediate casing including radial arms and a driveshaft for a gearbox for auxiliary machines of the turbojet engine, the driveshaft mounted in a radial arm, the radial arm including an intermediate bearing supporting the driveshaft, the intermediate bearing including plural rolling bearings supporting the driveshaft, the driveshaft including a first shaft element connected at one end to a mechanism providing mechanical transmission to an engine shaft of the turbojet engine, and a second shaft element connected at one end to a mechanism providing mechanical transmission to the box. The first shaft element and the second shaft element are linked by a connection including plural splines. A single plane transversely passes through the plural splines and the plural rolling bearings.

Driveshaft for the gearbox of auxiliary machines of a turbojet engine

A device for centring and guiding the rotation of a turbine engine shaft, in which the outer race of a bearing is retained axially upstream and downstream by a retaining mechanism cooperating with a bearing bracket and with a coupling mechanism including elastically deformable mechanism connecting the outer race to the bearing bracket, the retaining mechanism being separate from a protecting ring of the device. A method of assembling such a device is also described. The retaining mechanism is pre-assembled with the coupling mechanism prior to the final assembly of the coupling mechanism with the bearing bracket. The device and the method have the combined advantages of axially retaining the outer race in two opposing directions and having a particularly straightforward assembly.

Device for centring and guiding the rotation of a turbine engine shaft including improved means for retaining the external bearing ring

A device for uncoupling a bearing carrier in a turbomachine, the bearing carrier including an upstream part and a downstream part including a plurality of upstream orifices respectively facing a plurality of downstream orifices. The uncoupling device includes rupture screws each passing through an upstream orifice and a downstream orifice, and at least a mechanism for double centering of a rupture screw with respect to the upstream orifice and to the downstream orifice respectively. The mechanism for double centering is independent of the upstream and downstream parts of the bearing carrier and of the rupture screw, and is configured to collaborate with the upstream part of the rupture screw such that when the rupture screw breaks, the upstream part carries with it the mechanism for double centering. A turbomachine can include such an uncoupling device.

Device for uncoupling a bearing carrier

A dual-flow turbine engine including: a fan rotatably mounted on a fan shaft and a stationary structural element, the fan shaft and the structural element being connected to one another at an upstream bearing and at a downstream bearing via an upstream bearing bracket and a downstream bearing bracket, respectively; and a decoupling device surrounding the fan shaft, and including a set of attachment screws joining the downstream bearing bracket to the structural element and a set of fusible screws joining the upstream bearing bracket to the downstream bearing bracket. At least some of the fusible screws are arranged between at least some of the attachment screws over a single circumference surrounding the fan shaft.

Dual-flow turbine engine having a decoupling device

A system for securing first and second tubular coaxial components carrying a roller bearing is provided. The system includes a forcing nut mounted inside the coaxial components and axially abutting against the first component after screwing-in of the second component; and a locking pin for preventing unscrewing of the nut and being arranged between the nut and the first component. The system also includes a cylindrical sleeve being arranged between the pin and the first component, being secured axially relative to the first component, and including an axial stop against which the pin is applied; and first and second devices for linking the pin and the first component in rotation, respectively, with the sleeve.

System for securing two tubular components one in the other, carrying a roller bearing

An aeroengine fan casing is made of composite material including fiber reinforcement densified by a matrix. The casing is secured to at least one ring or ring sector that is situated on the inside face of the casing and that is mechanically connected to an equipment fastener part that is situated on the outside face of the casing, in particular for fastening an accessory gearbox.

Growing community of inventors

Vigneux sur Seine, France

Regis Eugene Henri Servant