Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: The invention relates to an afterbody (15) for a turbojet engine comprising an afterburner casing (16), a thermal protection liner (26), and a diaphragm-forming assembly (40) interposed between the liner and the casing, this assembly defining a flow area intended to be traversed by a ventilation stream (34). According to the invention, the assembly (40) includes two annular plates (46, 50) overlapping one another, each being perforated with a plurality of apertures (48, 52) and being mounted on the liner and the casing respectively, these apertures jointly defining the flow area of the assembly. Furthermore, the assembly (40) is designed such that the expansion of the liner causes an angular displacement of the plate (50) with respect to the plate (46), leading to an increase in the size of the flow area.

Abstract: Mounting an exhaust cone of composite material. The exhaust cone is mounted to extend an adapter ring and it is held in particular by elastic stress means that act axially.

Abstract: Device for mounting a dividing wall (112) for separating the main air stream and the bypass air in a bypass turbojet engine afterburner, comprising means of attaching the upstream end of this wall to a guide vane casing and means (150) for supporting the downstream end of this wall, these means being provided on flame holder arms (130) of the afterburner radially on the inside of the dividing wall.