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

Snecma

Snecma Moteurs

Other

Philippe Pierre Bouiller

Stephane Rousselin

Gilles Alain Charier

Jean-Pierre Ruis

Daniel Germain Kettler

Pierre-Yves Bourquin

Gerard E Jourdain

Michel Franchet

Fabrice Michel Cot

Bruno Albert Beutin

Serge Rene Morreale

Jacques Rene Bart

Stéphane Rousselin

Michel Gilbert Brault

Didier Escure

Claude G Corbin

Pierre Yves Bourquin

A turbomachine having a longitudinal axis, the turbomachine comprising an annular rotor centered on the longitudinal axis of the turbomachine, an annular stator disposed coaxially around the rotor, at least one ball bearing disposed on the rotor and rotatably supporting said stator, the inside of the rotor defining part of an oil enclosure for cooling and lubricating the balls of the bearing, an electricity generator having a secondary magnetic circuit secured to the stator and a primary magnetic circuit constrained to rotate with the rotor, and a detector device for automatically detecting ferromagnetic particles in the oil enclosure, said detector device being powered electrically by electromagnetic induction.

Turbomachine having a device for automatically detecting ferromagnetic particles in an oil enclosure

A two-spool bypass turbojet includes a low-pressure spool having a rear portion carrying a low-pressure turbine provided with a low-pressure rotor. The turbojet includes a support structure connected to a casing and to a rear bearing in which the rotor is mounted. The bearing can be situated in an enclosure including a liquid lubricant feed. The enclosure can be put to atmospheric pressure via an air feed pipe connected to the enclosure via a link. The turbojet further includes an electricity generator connected to the rear end of the low-pressure rotor that extends downstream from the link, which link is secured to the rotor and includes a device for guiding the liquid lubricant from the feed to the bearing.

Two-spool bypass turbojet with a rear electricity generator, and an air flow connection device and system

A turbomachine includes a high-pressure spool, an axial compressor of axis X mounted on a rotor and including a casing and at least one rear bearing disposed between the casing and the rotor of the compressor. The turbomachine further includes an electricity generator coaxial with the spool and including a primary magnetic circuit that is constrained to rotate with the rotor of the compressor and a secondary magnetic circuit that is secured to the casing. The electricity generator is disposed upstream from the rear bearing and includes at least a first cooling circuit surrounding the secondary magnetic circuit and extended by a nozzle for lubricating the rear bearing.

Turbomachine including an integrated electricity generator

A low-pressure turbine of a turbomachine, the turbomachine comprising a high-pressure turbine disposed upstream from the low-pressure turbine, and an exhaust casing disposed downstream from the low-pressure turbine, the low-pressure turbine comprising a rotor secured on a low-pressure trunnion, a low-pressure shaft, a first rolling bearing disposed on said low-pressure shaft and supporting a high-pressure trunnion having fastened thereon a rotor of the high-pressure turbine, a second rolling bearing disposed on said low-pressure trunnion downstream from said first rolling bearing and enabling said low-pressure trunnion to be centered relative to said exhaust casing, and a system of fluting for enabling said low-pressure trunnion to drive said low-pressure shaft, said system of fluting being disposed between said first and second rolling bearings.

Low-pressure turbine of a turbomachine

The invention relates to a system for driving an accessory, such as a fuel pump or an oil pump in a turboengine, said system comprising an electric motor and further comprising an air turbine associated with said electric motor. Said air turbine is suitable for being fed with a flow of air taken from a compressor of said turboengine and contributing to driving the accessory. The system also includes a valve for controlling the flow of air taken from the compressor, which valve is in the closed position while the turboengine is starting.

Assistance and emergency drive for electrically-driven accessories

An axially symmetric turbojet engine exhaust-nozzle includes a system for masking the exhaust jet, such system including inner hot flaps (,), hinging on a conical shell (,) and driven by a first control ring (,) powered by linear actuators (,), and outer cold flaps (,) hinging on an annular assembly (,) and driven by a second control ring (,) powered by linear actuators (,) to vary the angle of the cold flaps. The annular assembly (,) is axially displaceable by a third set of linear actuators (,). Each cold flap (,) comprises an inner skin (,) fitted with orifices (,) and hinging on the annular assembly(,) and an outer skin (,) spaced radially away of the inner skin (,) to define an air flow channel between the skins. When the annular assembly (,) is moved downstream by the third set of linear actuators (,), the outer skins (,) form a scoop introducing fresh air into the cold flaps (,), and said air is injected into the hot gas flow through the orifices (,) in the inner skin and other orifices (,) at the trailing edge (,) of the cold flaps to reduce the exhaust signature.

Turbo jet engine exhaust nozzle with masked gas jet

A gas-flow exhaust assembly for a jet propulsion system of an aircraft in which a converging exhaust nozzle (4) is fitted with translating cold flaps (21, 22). The primary exhaust nozzle (4) comprises two hot-flaps (5, 6) situated beyond a primary duct (1) enclosed by an aircraft fairing (2). The fairing (2) is extended by a secondary exhaust nozzle (20) which is supported by the primary duct (1) and which is translatable by a control mechanism (27a, 27b). The secondary exhaust nozzle (20) comprises cold flaps (21, 22) which are driven by another control mechanism (29a, 29b) independently of the angular positions of the hot flaps (5, 6). Preferably, there are two eyelid-shaped cold-flaps (21, 22) hinging and supported on horizontal transverse shafts (23a, 23b). The shafts (23a, 23b) are preferably affixed on two lateral slides (24a, 24b) which slide on the primary duct (1) and are displaceable by the control mechanism (27a, 27b) which translates the secondary exhaust nozzle (20).

Converging exhaust nozzle fitted with translating cold flaps

A variable geometry exhaust nozzle is disclosed for a turbojet engine having a rear portion, the nozzle having an outer flap ring with a plurality of driven outer flaps and a plurality of outer interlock flaps, each outer flap being pivotally connected to the rear portion of the turbojet engine, and an inner flap ring having a plurality of inner forward driven flaps and a plurality of inner forward interlock flaps, each having a forward portion pivotally attached to the rear portion of the turbojet engine, the inner flap ring also having a plurality of inner rear driven flaps and a plurality of inner rear interlock flaps, each inner rear flap having a front edge portion pivotally connected to a rear edge portion of a corresponding inner forward flap. The inner and outer flap rings are radially spaced apart and are arranged symmetrically about an axis of symmetry, with a drive collar located in the space between the inner and outer flaps that is movable between forwardmost and rearmost positions in a direction substantially parallel to the axis of symmetry of the nozzle. A plurality of translating levers are each pivotally attached to the drive collar and to one of the inner forward driven flaps. A plurality of interlock levers are each pivotally connected to one of the translating levers and to one of the inner rear driven flaps. Each interlock lever is connected to one of the outer driven flaps by a link rod pivotally connected to the interlock lever and to the outer driven flaps. Actuators are connected to the rear portion of the turbojet engine and to the translating levers to move the drive collar between its forwardmost and rearmost positions, such movement causing the inner flap ring to move between a converging-diverging configuration and a converging--converging configuration. Thus, the nozzle is suitable for both subsonic and supersonic aircraft operation.

Variable geometry turbojet engine exhaust nozzle

A turbojet having an air intake case including radial arms between an outer annular structure and an inner central structure, and a deicing unit configured to deice the radial arms by microwaves and located in the central structure. The deicing unit has a microwave generator and a transmitting element configured to transmit energy and including an inside annular waveguide located inside of the central structure. An energy distributing element configured to eliminate ice is coupled with the transmitting element by a coupling element. The radial arms are made from a dielectric composite material.

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Samoreau, France

Philippe Pierre Bouiller