Abstract: 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 F1 downstream from said upstream injectors.

Abstract: A system for controlling a flow of air applied to a gas turbine shroud in an airplane engine, the air flow being adjusted by a regulator valve of position that is controlled by a first control signal calculated on the basis of a first setpoint value corresponding to predetermined clearance between the rotor and the turbine shroud. The system further comprises means for calculating at least one second control signal based on a second setpoint value different from the first value representative of clearance in the turbine, and selector means for-selecting the second control signal to control the regulator valve in response to one or more engine parameters. With such a system, it is possible to control the air flow applied to the shroud in application of a plurality of control logic systems.

Abstract: A diffuser for a gas turbine engine, said diffuser being disposed between a last stage of a turbine and an exhaust casing, and comprising an outer annular wall and an inner annular wall together defining an annular passage for fluid that diverges in the flow direction of said fluid, at least one of the annular walls including a plurality of orifices leading from said annular passage to at least one collecting box leading to means for exhausting a fraction of said fluid so as to reduce the flow speed of said fluid in said annular passage.

Abstract: A device for axially retaining blades on a rotor disk of a turbomachine, the device comprising an annulus which is mounted via a radially inner edge in an annular groove of the disk and which presses against the roots of the blades mounted in grooves in the periphery of the disk, and an annular lock received in the annular groove of the disk to prevent the annulus from turning, said lock being turnable in the annular groove between an annulus-locking position and a position for mounting and dismounting in the annular groove.

Abstract: The invention concerns the mount for an aircraft engine arranged to be attached firstly by a beam to the aircraft, and secondly by lateral and a median load transmission elements to the engine, the mount comprising an integrated load transmission and failsafe assembly arranged to ensure the continuity of load transmission in the event of failure of a load transmission element and to perform its failsafe function in unitary, concentrated fashion in the median zone of the mount. The mount is characterized by the fact that the load transmission and failsafe assembly comprises an assembly of a female clevis with two wings and of a projecting element passing with clearance through the two wings of clevis, one being integral with the engine and the other with the mounting beam.

Abstract: The invention pertains to an engine mount onto an aircraft structure comprising at least one connection means between a first and a second element such as an engine case and said structure, characterized by the fact that said connection means comprises an eccentric member housed in a bore of the first element, being rotational about a first axis, the eccentric member comprising a trunnion attached to the second element and of axis off-centred with respect to the first axis of rotation, the eccentric member being rotational about said off-centred axis. The solution of the invention has the advantage of allowing a compact assembly.

Abstract: The retainer for fixing a long element (8) onto a surface comprises a retaining part (24, 28) which contains one long element (8), and at least one attachment flat (26). The retaining part (24, 28) is closed. It is preferably made from a material such that it can be attached by welding, and the attachment flats (26) comprise at least one lip (30).

Abstract: The invention provides a method of manufacturing or repairing a coating on a metallic substrate. Production of said coating comprises forming a pre-layer on the substrate or on a sub-layer of the coating placed on the substrate by applying one or more layers of a paint containing at least one metal selected from the group constituted by platinum class metals (platinoids) and chromium. Application to the formation or localized repair of a thermal barrier on a superalloy turbo engine part.

Abstract: The present invention relates to a TIG welding method of a first part with a first wall and an end edge to a second part with a second wall and an edge, both parts being welded to one another along a junction surface between said edges and along which the first wall forms a salient angle with the second wall. The method characterised in that the electrode is moved along said surface, the electrode being laid out on the side of the salient angle according to an angle (?) with respect to the first wall smaller than 180°, the direction (D) of the electrode running through the re-entrant angle associated with the salient angle. The method is applied in particular to the welding of plug guides to a combustion chamber jacket of a gas turbine motor.

Abstract: Turboshaft engine comprising two subassemblies defining between them an annular chamber housing a seal. The two subassemblies are assembled under axial stress thereby defining an annular chamber housing the seal and an interposed part is inserted between the butting surfaces of the two parts of the annular chamber.

Abstract: 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.

Abstract: A blade for a turbomachine gas turbine, the blade having a cooling circuit comprising at least one cooling cavity with a high aspect ratio extending radially between a root and a tip of the blade, and at least one air admission opening at a radially inner end of the cavity to feed it with cooling air, at least one of the walls of the cooling cavity being provided with a plurality of indentations so as to disturb the flow of cooling air in said cavity and increase heat exchange.

Abstract: A turbomachine comprising, downstream from the turbine, a post-combustion chamber defined by a thermal protection lining inside a casing defining an annular channel for a secondary flow, an annular diaphragm secured at the downstream end of said channel, said nozzle comprising a plurality of flaps hinged to the upstream end of said casing, each flap fitted on its inside face with a thermal protection plate to define a passage for cooling air delivered by said diaphragm, wherein the cooling air is provided by an annular duct defined by a first flexible annular gasket in sliding contact against the downstream inside face of the casing and against the upstream inside faces of the flaps under the pressure of the secondary flow, and defined on the inside by a second flexible annular gasket whose upstream end is fixed to the radially inner zone of the diaphragm, and whose downstream end is in sliding contact against the upstream inside face of the protection plates.

Abstract: The carbonization of cellulose fiber fabric comprises an initial stage of heat treatment up to 250° C. to 350° C., with a relatively high mean temperature rise speed of 10° C./min to 60° C./min, an intermediate stage up to 350° C. to 500° C. with a lower mean temperature rise speed of 2° C./min to 10° C./min, and a final stage up to 500° C. to 750° C. with a mean temperature rise speed that is again raised to 5° C./min to 40° C./min.

Abstract: A device for feeding air and fuel to a burner ring in an after-burner chamber comprises a plurality of flame-holder arms extending radially about the axis of the chamber from an outer casing, a burner ring made up of ring sectors mounted substantially end to end on the flame-holder arms, and means for feeding air and fuel to the burner ring sectors, said means extending between the burner ring and the outer casing of the after-burner chamber inside the flame-holder arms.

Abstract: The inventions refers to a method of manufacture of a multilayer ceramic shell mould whereof at least one contact layer, one intermediate layer and several reinforcing layers, out of a wax master pattern or other similar material, consists in performing the following successive operations: dipping in a first slip containing ceramic particles and a binder, depositing sand particles onto said layer and drying said contact layer, in order to form said contact layer, dipping in a second slip containing ceramic particles and a binder, depositing sand particles onto said intermediate layer and in drying said layer, in order to form said intermediate layer, dipping in at least a third slip containing ceramic particles and a binder, depositing sand particles onto said layer, drying said layer, in order to form a reinforcing layer, the formation of reinforcing layers being repeated until obtaining a shell mould of set thickness.

Abstract: The invention relates to a method for the three-dimensional measurement of coordinates (xli, yli, zli) of a set of N predetermined points (Plij) of the surface of a mechanical part to be measured, relatively to a predetermined reference system (Ro), and the direction cosines (cxthij) cythij, czthij) of the theoretical normals (Nthij) thereto at the theoretical points (Pthij) corresponding to said N predetermined points (Plij) are known, and including: a preparatory phase, in which the coordinates (xoij, yoij, zoij) of N points (Poij), corresponding to said N predetermined points (Plij) of the surface of a first mechanical part taken as a standard part, are measured relatively to the predetermined reference system (Ro), an initialization phase, in which N displacement measurements (loij) along said normals (Nthij) are simultaneously and respectively read on said N points (Poij) of said standard part, a measurement phase, in which N linear displacement measurements (llij), simultaneously and respectively perfor

Abstract: Pickling the inside and the outside of a hollow part that is in the form of a body of revolution, such as, in particular, a turbine wheel made of titanium alloy. The part is mounted with its axis of revolution in a horizontal orientation and it is partially immersed in a vessel filled with pickling composition while being caused to rotate about its axis of revolution.

Abstract: The drum of the invention is generally in the form of a body of revolution about a longitudinal axis, being made of a metal alloy and extending between an upstream end and a downstream end along a curved profile capable of being circumscribed in an annular envelope extending around said longitudinal axis, said profile extending radially about a surface of revolution presenting a generatrix line, said downstream end being provided with a stiffener. In characteristic manner, said stiffener is provided with at least one composite assembly mounted on said downstream end, said composite assembly comprising fibers and a polymer matrix. The drum is preferably for use in constituting a rotor of a low pressure compressor.

Abstract: The invention relates to a method of manufacture of a multilayer ceramic shell mould whereof at least one contact layer out of a wax master pattern or a part to be manufactured, or other similar material, consisting in dipping the master pattern in a first slip containing ceramic particles and a binder, in order to form said contact layer, in depositing the sable particles onto said layer and in drying said contact layer. The method is characterised in that the ceramic particles of the slip are mullite particles.