Safran Aircraft Engines

Snecma

Marc Jacky Vassault

Jean-Baptiste Mottin

Jean-Pierre Ferte

Richard Michael Coulette

Mathieu Gueguen

Pascal Jean-Christian Claude Ravault

Laurent Le Ber

Didier Brouard

According to the invention, a blade is friction-welded to a rotor disk of a turbomachine, the disk comprising a projecting block having an outer surface to which the blade is to be welded. To this end: a surfacing process is carried out on at least a part of the periphery of the block, in the region of said outer surface; the outer surface of the block and the surfacing are machined in order to level same; and friction-welding is then carried out between the surfaced outer surface of the block and the blade.

Method for friction-welding a blade to a turbomachine vane, including a surfacing process

A method and device for ultrasound testing of welds is provided. For testing element welds on a body forming a single-piece assembly with these elements, the free end of a poly-articulated robot is fitted with an ultrasound probe which is fitted with an ultrasonic multi-element array transducer; the probe is inserted into the space between two adjacent elements of the assembly; the probe is moved along three-dimensional trajectories along the profile of the element; sectorial electronic scanning is performed in at least two non-parallel testing planes; and ultrasound signals output by the transducer in order to test the welds are processed. The method and device may be applied to welds of blades on the blisk of a bladed disk.

Method and device for ultrasound inspection of welds, particularly welds of blades on the disk of a bladed disk

A method of friction welding an airfoil () onto a rotor disk of a turbine engine, the disk having at its outer periphery a projecting stub () onto which the airfoil is to be welded, the method comprising a step consisting in mounting chocks () on leading and trailing edges of the stub, the method being characterized in that, before friction welding, the chocks are secured to the stub by welding, and in that during the friction welding operation, the beads of welding () between the chocks and the stub are expelled, at least in part, in seams of material () that form around the connection zone between the airfoil and the stub and that are subsequently to be removed or eliminated, e.g. by machining.

Method for friction welding a blade onto a turbine engine rotor disc; corresponding integral blade disc

A system includes a unit of a first part, and a proximal portion through an intermediate portion extended by a distal portion including a first extremity surface. A second part with a second portion includes a second surface to be friction welded with the extremity surface. A second portion is bordered laterally by a lateral surface and has a proximal portion, which extends through an intermediate portion extended by a distal portion. The distal portion of the second portion is carried in a malleable state during a friction welding. The intermediate portion of the second portion flares from the distal portion by the second towards and till the proximal portion of the second portion such that the bead of material from the deformation of the distal portion of the second portion during welding rubs against the lateral surface of the intermediate portion of the second portion during welding.

Parts assembled through friction welding

The invention concerns a method of recuperating a turbine element constituted of a substrate, forming the body of the element, and a protective coating adhering to the substrate. The method comprises the control of the turbine element in order to pinpoint the zones having a bonding defect between the protective coating and the substrate, and the elimination of the bonding defects between the protective coating and the substrate. The bonding defects are eliminated by means of a laser beam directed onto each zone having a bonding defect in order to induce a localized melting of the protective coating and the underlying substrate and enable a sound bond, at the level of said zone, between the protective coating and the substrate after stopping the laser beam.

Method of recuperating turbine elements

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.

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Evry, France

Marc Jacky Vassault