Abstract: A method of assembling together titanium parts and steel parts by diffusion welding, the method interposing two thin layers of niobium or vanadium and copper respectively between a titanium part and a steel part, evacuating the assembly of parts and interposed metal layers, and subjecting the assembly to hot isostatic compression at a temperature lying in a range 900° C. to 950° C. and at a pressure lying in a range 1000 bars to 1500 bars for about two hours. The method can be applied to fabricating turbine shafts for turbomachines.

Abstract: A method of assembling together titanium parts and steel parts by diffusion welding, the method interposing two thin layers of niobium or vanadium and copper respectively between a titanium part and a steel part, evacuating the assembly of parts and interposed metal layers, and subjecting the assembly to hot isostatic compression at a temperature lying in a range 900° C. to 950° C. and at a pressure lying in a range 1000 bars to 1500 bars for about two hours. The method can be applied to fabricating turbine shafts for turbomachines.

Abstract: A process for resurfacing a monocrystalline or directionally solidified metallic piece, having a thickness (Ws), in which a laser beam and a flux of metallic powder, whereof the nature is the same as that of the metallic piece, is applied to the piece to produce at least one layer of metal, monocrystalline or directionally solidified, from the piece, the laser beam being sent out at a power “P”, and moving along the piece at a speed “v”, wherein the laser beam and the flux of powder are applied coaxially on the piece and the P/v ratio is within the range defined on the figure.

Abstract: A method of assembling together one-piece bladed disks by friction welding, and a damper device for damping vibration of the blades of the disks. The damper device includes annular linings for covering the blades and filling the gaps between the blades, the linings being made of elastomer and being held and clamped when mounted on the blades.

Abstract: The invention relates to a method of manufacturing a hollow blade for turbine engine comprising a foot and a rotor blade, the method comprising a production stage of two external parts (14) as well as an assembling stage via diffusion bonding of these two external parts so as to obtain a blade preform.

Abstract: A process for resurfacing a monocrystalline or directionally solidified metallic piece, having a thickness (Ws), in which a laser beam and a flux of metallic powder, whereof the nature is the same as that of the metallic piece, is applied to the piece to produce at least one layer of metal, monocrystalline or directionally solidified, from the piece, the laser beam being sent out at a power “P” and moving along the piece at a speed “v”, wherein the laser beam and the flux of powder are applied coaxially on the piece and the P/v ratio is within the range defined on the figure.

Abstract: A monobloc bladed disc and a process for manufacturing or repairing a monobloc bladed disc, where the process includes forming, on a protruding projection belonging to a disc and extending from an upstream end to a downstream end along a protruding projection chord, a welded joint surface intended to allow a subsequent stage of fitting a blade by linear friction welding onto the protruding projection of the disc. The forming the welded joint surface is carried out in such a way that it includes at least two butt-jointed plane portions arranged in sequence along the protruding projection chord.

Abstract: The invention relates to a friction plug welding method for a hole in a metal part, opening out onto a front surface and a back surface of the part, in which a rotational metal bar is inserted into the hole, on its front side, to be friction welded. The method according to the invention is characterised in that a restraint part, comprising a cavity, is placed on the back side of the part during friction welding. The method according to the invention authorises the welding of fast softening materials whilst ensuring a support for the weld mix.

Abstract: A turbomachine blade includes a metal alloy airfoil having a cavity closed off by a cover on a hollowed side, the cover providing aerodynamic continuity of the hollowed side and being bonded via an edge thereof to the rest of the airfoil by a weld bead. The weld bead emerges on the hollowed side and penetrates into the airfoil to a depth P at least equal to the thickness EC of the edge of the cover so as to provide continuity of material between the edge of the cover and the rest of the airfoil over a depth at least equal to the thickness EC of the edge of the cover. A process for manufacturing such a blade is also disclosed.

Abstract: A method of assembling together one-piece bladed disks by friction welding, and a damper device for damping vibration of the blades of the disks, the device comprising annular linings for covering the blades and filling the gaps between the blades, the linings being made of elastomer, and means for holding and clamping the linings when mounted on the blades.

Abstract: A turbomachine blade includes a metal alloy airfoil having a cavity closed off by a cover on a hollowed side, the cover providing aerodynamic continuity of the hollowed side and being bonded via an edge thereof to the rest of the airfoil by a weld bead. The weld bead emerges on the hollowed side and penetrates into the airfoil to a depth P at least equal to the thickness EC of the edge of the cover so as to provide continuity of material between the edge of the cover and the rest of the airfoil over a depth at least equal to the thickness EC of the edge of the cover. A process for manufacturing such a blade is also disclosed.

Abstract: The invention concerns a friction plug welding method, for a hole, extending globally along an axis, in a metal part, failing any clearance space in the axis of the hole, because of at least one obstacle on said axis, wherein a metal bar, extending globally along an axis, is rotated around its axis and is inserted into the hole, to be friction welded therein. The method of the invention is characterised in that the axis if the bar is tilted with respect to the axis of the hole of a non-zero angle (?) to avoid the obstacle. Thus, thanks to the method of the invention, it is possible to reach holes difficult of access, while orienting the axis of the bar suitably.

Abstract: The invention relates to a process for manufacturing or repairing a monobloc bladed disc including a stage of forming, on a protruding projection (4) belonging to a disc (1) and extending from an upstream end (4a) to a downstream end (4b) along a protruding projection chord (6), a welded joint surface (8) intended to allow a subsequent stage of fitting a blade (2) by linear friction welding onto the protruding projection (4) of the disc (1). According to the invention, the stage of forming the welded joint surface (8) is carried out in such a way that it includes at least two butt-jointed plane portions (8a, 8b, 8c), arranged in sequence along the protruding projection chord (6). Application to turboshaft engine rotors.

Abstract: The invention relates to a method of manufacturing a hollow blade for turbine engine comprising a foot and a rotor blade, the method comprising a production stage of two external parts (14) as well as an assembling stage via diffusion bonding of these two external parts so as to obtain a blade preform. According to the invention, the production stage of the two external parts comprises, for each of these parts, the following operations: the making via forging of a primary element (28) constituting at least a rotor blade part of the external part; the making via forging of at least a secondary element (34) intended to form at least partially a foot part of the external part; and the assembling of each secondary element (34) onto the primary element so as to obtain the external part.

Abstract: A tool for holding a blade blank (1) comprises a frame (13) in which a control system using clamping jaws (18, 19) and lifters (30, 34, 35) grips the blade and holds it in position vertically on two supporting faces (22, 23), while the blade has been laid on three lateral faces (41, 42, 43). The blade is thus simultaneously held in a precise position and gripped sufficiently tightly, with a single control main mechanism. The mounting of the blade is thus greatly simplified and it may be subjected without further precaution to a manufacturing operation such as welding by friction to a rotor disk.

Abstract: A tool for holding a blade blank (1) comprises a frame (13) in which a control system using clamping jaws (18, 19) and lifters (30, 34, 35) grips the blade and holds it in position vertically on two supporting faces (22, 23), while the blade has been laid on three lateral faces (41, 42, 43). The blade is thus simultaneously held in a precise position and gripped sufficiently tightly, with a single control main mechanism. The mounting of the blade is thus greatly simplified and it may be subjected without further precaution to a manufacturing operation such as welding by friction to a rotor disk.

Abstract: A process for assembling titanium aluminide articles by diffusion brazing comprises the following steps: (a) Preparation of a homogenous mixture of a titanium aluminide powder A of 40 to 90 weight % and a powder B chemically wetting A and having an appreciably lower melting point; (b) formation of a paste by addition of an organic binder to the powder mixture; (c) depositing the paste plumb on the assembly gap; and, (d) heating the assembly in a vacuum furnace between 1000° C. and 1300° C. for a period of from a few minutes to 6 hours. This process is also of use for repairing and refacing titanium aluminide articles.

Abstract: A method of producing a coating layer on a localized area of a superalloy component comprises the steps of:a) producing a coating layer element with specific functional properties;b) depositing on at least one surface of the coating layer element a uniform layer obtained from a powder mixture consisting of a powder of a nickel or cobalt superalloy and a powder of a brazing filler metal;c) brazing the coated composite coating layer element obtained from step (b) on to the localized area of the component; and,d) machine finishing the component.

Abstract: Process for welding two blade parts (9, 10) by a means such as a linear friction welding machine, in which a collar or flange (15) of material to be sacrificed is placed between the contact surfaces (16) or around the latter in order to increase the heat produced by the friction at the leading and trailing edges of the blade. As a result of this arrangement it is possible to start with two blade parts (9, 10) having the dimensions of the finished product, possibly with the exception of the area around the contact surfaces, so that the final machining is very significantly reduced.

Abstract: A method and an apparatus for friction welding two elements together are disclosed in which the areas of the two elements to be welded are heated by an induction heater. The induction heater may be used to heat the areas to be welded prior to contact between the elements, during such contact, and after the friction welding has been achieved in order to provide a heat treatment of the welded zone. The induction heater is generally annular in shape and may be dimensioned so as to be located around the elements at the welding zone, or to be placed between the surfaces of the elements to be welded together.