Snecma

Snecma Moteurs

Safran Aircraft Engines

Alain Pierre Page

Jacques Marcel Arthur Bunel

Thomas Daris

Jackie Raymond Prouteau

Jackie Raymond Julien Prouteau

Jacques Roche

Edgar Brunet

Jacques Andre Michel Roche

Sébastien Baboeuf

Jacques-A Roche

Jacques Marcel Bunel

Stephane Pierre Guillaume Blanchard

Mathieu Dakowski

Nicolas Pommier

Laurent Bernard Cameriano

Stephane Henri Guy Touchaud

Yann Vuillemenot

Jackie Prouteau

Thierry Cortes

Yann Francois Jean-Claude Vuillemenot

Jacques André Michel Roche

Eric Maingre

Frederic Schenher

Sabine Charpenel

Marc Doussinault

Fabienne Vagner

Thierry Andre Emmanuel Cortes

Stephane Henri Touchaud

Stephane Pierre Blanchard

Thierry Andre Cortes

Marc Emmanuel Doussinault

Thierry André Emmanuel Cortes

Vagner Fabienne

Frédéric Schenher

A device for mounting a dividing wall for separating the main air stream and the bypass air in a bypass turbojet engine afterburner is disclosed. The device includes an attachment unit which attaches the upstream end of the wall to a guide vane casing and a supporting unit which supports the downstream end of the wall provided on flame holder arms of the afterburner radially on the inside of the dividing wall.

Device for mounting an air-flow dividing wall in a turbojet engine afterburner

An afterbody for a turbojet engine is disclosed. The afterbody includes an afterburner casing, a thermal protection liner, and a diaphragm-forming assembly interposed between the liner and the casing. The diaphragm-forming assembly defines a flow area which is traversed by a ventilation stream. The diaphragm-forming assembly includes two annular plates overlapping one another, each being perforated with a plurality of apertures and being mounted on the liner and the casing respectively. The apertures jointly define the flow area of the assembly. Furthermore, the assembly is designed such that the expansion of the liner causes an angular displacement of the plate with respect to the plate, leading to an increase in the size of the flow area.

Turbojet engine comprising an afterburner duct cooled by a variable-throughput ventilation stream

An exhaust cone of composite material. The exhaust cone is mounted to extend an adapter ring and it is held by an elastically deformable element that acts axially.

Exhaust cone for channeling a stream of gas downstream from a turbine

A propulsion gas exhaust assembly in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator is disclosed. The exhaust assembly includes a duct which forms a vertical elbow and a nozzle.

Exhaust assembly forming a horizontal propulsion gas elbow in an aircraft

The present invention relates to a thrust orienting nozzle, shaped in such a way as to divide a principal propulsion gas flow coming from at least one gas generator into a first flow and a second flow for an ejection in a first half-nozzle and in a second half-nozzle and comprising at least one of following two piloting means: a means of dividing the principal flow into each of the two half-nozzles, and a means of orienting the thrust vector produced by each of the two half-nozzles. The invention applies in particular to the yaw control of an aircraft without a vertical tail unit.

Thrust orienting nozzle

The turbojet of the invention includes a combustion chamber, a channel for heating the gas stream, where the heating channel includes at least one device for injection of fuel into the gas stream, which includes an open chamber, with a U-shaped section, having at least one wall within which extend fuel-injection means, which inject the fuel in at least one direction. It is characterised by the fact that a cooling jacket is provided in the chamber, alongside the wall forming the base of its U-section, and the fuel injection device includes protection means interposed between the fuel-injection means and the wall, in a fuel-injection direction. Thus, as a result of the invention, the fuel injection device, which is bathed in a very hot environment, is protected against thermal shocks due to the projection of colder fuel onto its walls, and its life expectancy is therefore increased.

Turbojet with protection means for a fuel injection device, an injection device and a protective plate for the turbojet

The after-burner device receives a 'hot' central primary flow from the turbine of the turbojet and a 'cold' peripheral secondary flow, and it has an after-burner ignition zone situated in the secondary flow that reaches the after-burner device. A fraction of the primary flow is brought into the after-burner ignition zone in order to raise the temperature in said zone to a value that is higher than that of the secondary flow so as to encourage after-burner ignition.

Method of improving the ignition performance of an after-burner device for a bypass turbojet, and an after-burner device of improved ignition performance

A propulsion gas exhaust assembly is presented for use in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator. The assembly may include a first cylindrical duct, two second ducts, two third ducts, and two axial gas-ejection nozzles. The first cylindrical duct element receives the gases downstream of the gas generator. The gasses flow downstream from the first cylindrical duct element to two second duct elements. These two second duct elements are divergent in a first geometric plane. Each of the two second duct elements may guide the flow to their own respective third duct and nozzle. The third ducts may include elbows to assist in stealth. The nozzles may include the means to steer the aircraft.

Elbow-shaped propulsion gas exhaust assembly in an aircraft

A double flow turbo-jet engine includes a re-heating channel of the primary flow and an ejection nozzle, the secondary flow emerging at least partially in the primary flow upstream of the re-heating channel, the re-heating channel including a burner ring, including a flame holder gutter in the form of a ring portion whereof the upstream section is situated in the secondary flow, receiving a fuel manifold and a protective tubular screen of the manifold. The gutter includes an upstream recess linked with the secondary flow, and the screen includes, on its upstream section, at least one ventilation orifice of the space situated between the screen and the manifold.

Turbo-jet engine with a protective screen of the fuel manifold of a burner ring, the burner ring and the protective screen

The invention relates to ventilating the confluence sheet of an afterburner chamber of an aviation turbomachine, including, upstream from the afterburner chamber: a diffuser defined by a confluence sheet disposed inside a casing, said casing and said confluence sheet defining between them an annular channel for a cold secondary flow, upstream fuel injectors being disposed at the inlet to said diffuser and flame-catchers being disposed downstream from said upstream injectors, said confluence sheet presenting, between the radial plane containing said upstream injectors and the radial plane situated at the rear ends of said flame-catchers two bends so as to flare downstream in order to slow down the primary flow Fdownstream from said upstream injectors. An annular scoop is provided around the upstream portion of said confluence sheet in order to extract a flow of air from the cold flow, said extracted flow being injected tangentially into the primary flow via a plurality of channels formed in the wall of said confluence sheet between the scoop and said diffuser.

Ventilation channels in an afterburner chamber confluence sheet

Growing community of inventors

Montgeron, France

Alain Pierre Page