Abstract: A dobby includes two controlled latches for coupling a drive element mounted to a main drive shaft of the dobby and an actuator element in rotation. A first resilient element resiliently biases each of the latches towards a configuration in which their respective bearing surfaces are engaged with corresponding surfaces of the actuator element. Control members are provided for moving the latches against the action of the first resilient element and that act directly on the first latch and indirectly on the second latch so as to move the first latch against the first resilient element to thereby disengage its bearing surface with a corresponding surface of the actuator element while the second latch remains in a configuration in which its bearing surface is engaged with another corresponding surface of the actuator element.

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: The object of the present invention is mainly a powder dispenser including a casing capable of impulsing the powder in a reciprocal movement on a plane along a determined displacement direction (X), and means (19,23) for grouping the powder along distinct axes, substantially parallel to the X direction. The object of the present invention is also a method for making pellets, notably nuclear fuel pellets, applying a dispenser according to the present invention.

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 lever (11) is fitted with two rollers (20A, 20B) which are supported by a core (21) provided with a mounting bore (21B) on an articulated shaft, wherein the rollers (20A, 20B) are both mounted between two webs of a pair of webs which are added to the core (21). The webs (22A, 23B) are on the whole planar. A first web (22A) of each pair of webs is partially engaged in a hollow housing (21C) created on the lateral surface (21D) of the core (21). The second web (23B) of the same pair is maintained at a distance from the first web. The hollow housings (21C) are created on the two opposite lateral surfaces (21D) of the core (21) of the lever (11).

Abstract: Device comprising means of separating at least two sintering shoes for transporting nuclear fuel pellets capable of moving according to a first axis (X) and of which two end faces are in contact with one another, wherein said separating means are capable of moving at least one of the two sintering shoes close to said end faces in contact, according to a second vertical axis (Y) substantially orthogonal to the first axis (X).

Abstract: According to the invention, a mandrel, provided with tabs for holding jars containing powders and for turning the jars upside down in order to empty them through the neck, is equipped with vibration generators for exciting the walls of the jar in order to shake off the powder masses adhering thereto. The method is much more efficient than even more energetic shock applications, and frequency scanning can further be advantageously applied. One application relates to an emptying step in methods for the production of nuclear fuel pellets by powder agglomeration.

Abstract: The object of the present invention is mainly a powder dispenser including a casing capable of impulsing the powder in a reciprocal movement on a plane along a determined displacement direction (X), and means (19,23) for grouping the powder along distinct axes, substantially parallel to the X direction. The object of the present invention is also a method for making pellets, notably nuclear fuel pellets, applying a dispenser according to the present invention.

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: A cam motion machine that includes several cams each defining at least one running track for a follower roller. Each cam is provided with a centering bore that permits mounting of the cam on a drive shaft, while elements are provided to apply a tightening force parallel to the drive shaft with a non-circular section. At least one washer-spacer, for which an internal edge is non-circular and designed to enable an axial displacement of the washer-spacer along the shaft, is fixed to rotate with the shaft and is in contact with at least one of the cams. The washer-spacer may be fixed to the cam by adherence and to the shaft by cooperation of shapes due to complementary projections provided on one of the shaft and the washer-spacer. It would be appreciate if the Examiner would indicate the acceptance of this amendment to the Abstract in the next office communication.

Abstract: The lever (11) is fitted with two rollers (20A, 20B) which are supported by a core (21) provided with a mounting bore (21B) on an articulated shaft, wherein the rollers (20A, 20B) are both mounted between two webs of a pair of webs which are added to the core (21). The webs (22A, 23B) are on the whole planar. A first web (22A) of each pair of webs is partially engaged in a hollow housing (21C) created on the lateral surface (21D) of the core (21). The second web (23B) of the same pair is maintained at a distance from the first web. The hollow housings (21C) are created on the two opposite lateral surfaces (21D) of the core (21) of the lever (11).

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: A heald frame including two posts, two cross members and connectors which are used for securing at least one post to at least one corresponding cross member. Each connector includes an intermediate tubular fixing element which is disposed in a housing provided in the cross member and indented with respect to a front face of the cross member and which element defines an internal volume in which a protrusion extending from the at least one post is seated.

Abstract: This dobby includes two controlled latches (10, 11) for coupling a drive element (8) and an actuator element (4) in rotation. First means (19) enable each of the latches (10, 11) to be resiliently biased (F19) towards a configuration in which their respective bearing surfaces (103, 113) are engaged with a corresponding surface (84A, 84B) of the actuator element (8). Control means (13, 14) are provided for moving the latches against the action of the resilient bias means (19) and that act directly on the first latch (10) and indirectly on the second latch (11). The control means can move (C14) the first latch (10) against the resilient bias means (19) while the second latch remains in a configuration in which its bearing surface (113) is engaged with the second surface (84B) of the actuator element (8).

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.