Abstract: The invention relates to a method of manufacturing a hollow metal blade, comprising at least one side wall and a recessed tip cap, characterized in that: a) a hollow blade, which comprises at least one side wall and the tip of which is open, is manufactured by casting; b) a plate of a laminate, comprising at least the metal of the blade and a brazing material, is manufactured; c) the plate is brazed to the top of the side wall of the blade by pressing the plate onto the blade; and d) the recessed tip cap, comprising at least a bottom and at least a squealer tip, is machined in the plate. Thanks to the invention, since the blade is manufactured beforehand with an open tip, the core can be held in place, during the casting operation, by the top, thereby ensuring great precision in the positioning of the core and therefore in the thickness of the walls of the blade. The invention also relates to a method of repairing a blade.

Abstract: The present invention relates to a method of repairing a one-piece bladed disc or blisk of turbomachine having at least one damaged zone, by build-up of metal in said damaged zone by means of a build-up welding machine, which comprises the steps of preparing the damaged zone, of building up the zone with metal and of re-work of the repaired zone. The method is characterized in that: the preparation step comprises the machining of the zone so as to obtain a defined profile; the build-up welding operation is carried out on a test piece, called start-of-run test piece, having said defined profile, using a build-up welding machine, which is a laser-type machine and the operating parameters of which are preset; the quality of the test piece after build-up welding is checked; and, if the quality of the test piece corresponds to the acceptance criteria, the zone to be repaired is built up using the same machine without changing the operating parameters thereof.

Abstract: In order to enable the information contained in an identification connector to be read in a manner that is more reliable, faster, and without risk of damage, the invention provides a reader appliance for reading identification connectors for airplane engines, the connector comprising a plurality of contacts connected to a decoding circuit, each contact corresponding to a binary digit, one or more of the binary digits corresponding to information relating to characteristics of the engine. The reader appliance comprises connection means suitable for receiving at least one identification connector, the connection means being connected to processor means responding to control members in order to display on a display device the information contained in the connector.

Abstract: The invention relates to a novel self-lubricating solid material; to a method of preparing such a material from a powder mixture; to said powder mixture; and to mechanical parts made of said novel material. Said powder mixture comprises a powder of a metal alloy that is a precursor for the matrix of said material, particles of a first solid lubricant such as CeF3 that are for insertion in said matrix without reacting with said metal alloy, and particles of a second solid lubricant such as WS2 or MoS2 for reacting with a component of said metal alloy during sintering of the powder to form a lubricating phase. Said material can be used for fabricating a bushing that is to receive a root of a variable-pitch vane of an airplane turbojet compressor.

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 method of locally repairing parts coated with a thermal barrier including a ceramic outer layer and a metal underlayer of alumina-forming alloy for protecting the substrate against oxidation and for bonding with the ceramic outer layer, includes: defining the zone for repair with a mechanical mask adapted to the shape of the part and the zone for repair; scouring the zone for repair so as to remove the ceramic, the alumina layer, and the damaged portions of the underlayer; supplying materials for repairing the underlayer to the repair zone by subjecting the partially-scoured part to metal deposition by use of an electrical current; and subjecting the part to a heat treatment in order to enable the added metals to diffuse into the remaining underlayer in the repair zone for repair and to enable a surface film of alumina to form. After the underlayer has been reconstituted, the zone for repair is again defined by a mechanical mask and a new ceramic layer is deposited thereon.

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 present invention relates to management of machine servicing, particularly, but not only, aircraft engine servicing. When a machine is received in a service facility for one of a plurality of predefined reasons, repair and/or maintenance procedures known to correspond to that reason are identified and a workscope defining work to be performed is generated. It is desirable (but not required according to the present invention) to identify what parts and/or tools will be needed to carry out the repair and/or maintenance procedures. It is additionally desirable to permit the parts and/or tools to be ordered or otherwise requested in anticipation of carrying out the defined work. The workscope can be enhanced by taking into account work (required or not) that is customarily performed for a given client.

Abstract: Apparatus for searching for and detecting defects on parts that are substantially inaccessible, being located behind a wall, the apparatus comprising a first endoscope for illumination in visible light and for observation, the first endoscope and pipes for feeding and spraying penetration test substances being housed together in a rod which can be passed through an orifice in the wall in order to examine a part, the apparatus further comprising a second endoscope independent of the first endoscope and the rod for illuminating in ultraviolet light and for observing the portion of the part that has been treated by the penetration test substances.

Abstract: A method and system for detecting damage to the rotor of an aircraft engine using devices for measuring vibration and speed in order to acquire data relating to the speed of the rotor and also to the amplitude and the phase of rotor vibration during a determined flight. The method includes the following steps: reading the acquired data; calculating a mean vibration vector over a determined rotor speed range on the basis of the acquired data; calculating a vector difference between the mean vibration vector of the determined flight and the mean vibration vector of a reference flight for the rotor speed range; comparing the modulus of the vector difference with a predetermined threshold value; and issuing a warning signal when the modulus of the vector difference exceeds the predetermined threshold value, the steps being performed after the determined flight has been completed.

Abstract: The invention relates to a device and a method for control of the operation of a thermal projection torch (12), characterized in that the characteristics of the jet (16) and the temperature of the deposit (24) on the piece (22) are measured by means of a camera (54) and a combined pyrometer (70). The correction to be made to the supply parameters of the torch (12) are deduced therefrom and the corrected parameters are transmitted to the unit (30) controlling the torch (12).

Abstract: The present invention provides: a material, which is dense, with a density of ?90%, bulk dry self-lubricating, with a coefficient of friction of <0.3, constituted by a matrix that endows it with suitable strength, with a Rm of ?400 MPa in a medium to high temperature range of 300° C.???600° C.; said matrix including particles of solid lubricant in its volume; mechanical parts formed from said material; a method of manufacturing said material.

Abstract: The invention relates to a ceramic thermal barrier composition of low conductivity and high high-temperature strength. In characteristic manner, the composition comprises a zirconia base, at least one trivalent oxide enabling the zirconia to be stabilized and enabling the thermal conductivity of the zirconia to be reduced in optimum manner, and at least one pentavalent oxide enabling the content of oxygen vacancies to be reduced so as to make it substantially equal to that of a partially stabilized zirconia. Preferably, said trivalent oxide is present with a molar content constituted by a first portion enabling the zirconia to be stabilized partially and a second portion which introduces point defects into the lattice said pentavalent oxide is present with a molar concentration equal to said molar concentration of said second portion of the trivalent oxide. The invention is applicable to making a superalloy machine part having a ceramic coating with said composition, and possibly also a bonding underlayer.

Abstract: A simple and low cost method of replacing an abradable portion on the fan casing of a turbojet includes an inside heating belt together with holding sectors therefor are put into place against the abradable portion, each holding sector including an inflatable bladder, and the abradable portion and the inside heating belt being sandwiched in full between the fan casing and the bladders, the holding sectors themselves being held in place by a plurality of straps attached to the fan casing by fixing points.

Abstract: In order to enable the information contained in an identification connector to be read in a manner that is more reliable, faster, and without risk of damage, the invention provides a reader appliance for reading identification connectors for airplane engines, the connector comprising a plurality of contacts connected to a decoding circuit, each contact corresponding to a binary digit, one or more of the binary digits corresponding to information relating to characteristics of the engine. The reader appliance comprises connection means suitable for receiving at least one identification connector, the connection means being connected to processor means responding to control members in order to display on a display device the information contained in the connector.

Abstract: The invention relates to detecting damage to the rotor of an aircraft engine that includes means for measuring vibration and speed in order to acquire data relating to the speed of the rotor and also to the amplitude and the phase of rotor vibration during a determined flight. The method comprises the following steps: reading said acquired data; calculating a mean vibration vector over a determined rotor speed range on the basis of said acquired data; calculating a vector difference between the mean vibration vector of said determined flight and the mean vibration vector of a reference flight for said rotor speed range; comparing the modulus of said vector difference with a predetermined threshold value; and issuing a warning signal when the modulus of said vector difference exceeds said predetermined threshold value, said steps being performed after said determined flight has been completed.

Abstract: The present invention concerns:

Abstract: The present invention provides:

Abstract: A diffusion-brazing filler powder for a part made of a nickel-, cobalt- or iron-based alloy A comprising particles of a defined alloy material B having specific functional properties tailored to the area of application of said part. The particles are substantially spherical and carry, on their surfaces, in the form of incrustations, add-ons comprising at least one fluxing element taken from the group: boron and silicon, these encrusted add-ons also being present in a free state in said powder.

Abstract: A method for extending the life of the attachments that attach blades to rotors, particularly for aerojet engines. Such a method is notable in that it employs intensive ultrasonic peening of the grooves and of the roots of the blades, this peening being performed with an Almen intensity at least equal to F8A, so as to increase the compressive prestress in the contact surfaces without increasing the roughness of these surfaces.