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

Snecma Moteurs

Other

Snecma

Jean-Pierre Ruis

Philippe Pierre Bouiller

Daniel Germain Kettler

Pierre-Yves Bourquin

Michel Franchet

Fabrice Michel Cot

Gerard E Jourdain

Marcel R Soligny

Philippe Pierre Vincent Bouiller

Michel Francois Raymond Franchet

Pierre Yves Bourquin

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

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 electrohydraulic device for varying the pitch of the blades of a machine rotor, the blades being mounted on a hub rotated by a drive shaft of the machine, and each blade having a root capable of pivoting about a longitudinal axis of the blade, the drive shaft itself being rotated relative to a stationary structure of the machine, the device comprising firstly a hydraulic actuator whose piston is secured to a control and synchronization ring in which off-center wrist pins are engaged, each fixed in register with one of said blade roots, and having a cylinder closed by a cover that includes a high pressure hydraulic pump feeding hydraulic fluid to both faces of said piston via channels integrated in said cylinder of the actuator, and secondly an electric motor controlled and powered by an electricity generator comprising an inductor secured to said stationary structure of the machine and an armature secured to said drive shaft of the machine.

Electrohydraulic device for varying the pitch of the blades of a machine rotor

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 turbine plant intake housing includes an outer shell supporting radially extending arms which include a fixed part and a movable flap associated therewith. Each arm is provided with a metal tie rod having its radially outer end fixed between two forks supported by the outer shell, and its radially inner end co-operating with a metal insert embedded in layers of coiled filaments of composite material forming a floating hub supported by the tie rods. The radially inner end of each rod is attached to the insert of the hub by use of a nut which effects a prestressing clamping of the tie rod on assembly.

Turbine plant intake housing

A device for attaching the stator vanes of an axial compressor to an external housing is disclosed. The attachment utilizes an inner casing, having the vanes mounted on it, and an outer casing surrounding the inner casing in such a manner that differential thermal expansion between the various elements is minimized. This allows more accurate control of the clearances between the rotor and the stator.

Growing community of inventors

Le Chatelet en Brie, France

Jean-Pierre Ruis