Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/24—Heat or noise insulation
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
  • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
  • B23K26/12—Working by laser beam, e.g. welding, cutting or boring in a special atmosphere, e.g. in an enclosure
  • B23K26/123—Working by laser beam, e.g. welding, cutting or boring in a special atmosphere, e.g. in an enclosure in an atmosphere of particular gases
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
  • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
  • B23K26/14—Working by laser beam, e.g. welding, cutting or boring using a fluid stream, e.g. a jet of gas, in conjunction with the laser beam; Nozzles therefor
  • B23K26/1462—Nozzles; Features related to nozzles
  • B23K26/1464—Supply to, or discharge from, nozzles of media, e.g. gas, powder, wire
  • B23K26/147—Features outside the nozzle for feeding the fluid stream towards the workpiece
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
  • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
  • B23K26/20—Bonding
  • B23K26/21—Bonding by welding
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
  • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
  • B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
  • B23K35/38—Selection of media, e.g. special atmospheres for surrounding the working area
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
  • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
  • B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
  • B23K35/38—Selection of media, e.g. special atmospheres for surrounding the working area
  • B23K35/383—Selection of media, e.g. special atmospheres for surrounding the working area mainly containing noble gases or nitrogen
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
  • B23K9/00—Arc welding or cutting
  • B23K9/16—Arc welding or cutting making use of shielding gas
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
  • B23K9/00—Arc welding or cutting
  • B23K9/16—Arc welding or cutting making use of shielding gas
  • B23K9/164—Arc welding or cutting making use of shielding gas making use of a moving fluid
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
  • B23K9/00—Arc welding or cutting
  • B23K9/32—Accessories
  • B23K9/325—Devices for supplying or evacuating shielding gas
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
  • B23P6/00—Restoring or reconditioning objects
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
  • B23P6/00—Restoring or reconditioning objects
  • B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
  • B23P6/005—Repairing turbine components, e.g. moving or stationary blades, rotors using only replacement pieces of a particular form
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B15/00—Layered products comprising a layer of metal
  • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B43/00—Operations specially adapted for layered products and not otherwise provided for, e.g. repairing; Apparatus therefor
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
  • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
  • B64F5/40—Maintaining or repairing aircraft
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/005—Repairing methods or devices
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
  • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
  • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
  • F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
  • F16B5/01—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening elements specially adapted for honeycomb panels
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
  • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
  • F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
  • F16B5/08—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of welds or the like
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
  • B23K2101/00—Articles made by soldering, welding or cutting
  • B23K2101/006—Vehicles
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
  • B23K2101/00—Articles made by soldering, welding or cutting
  • B23K2101/02—Honeycomb structures
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
  • B23K2103/00—Materials to be soldered, welded or cut
  • B23K2103/08—Non-ferrous metals or alloys
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
  • B23K2103/00—Materials to be soldered, welded or cut
  • B23K2103/08—Non-ferrous metals or alloys
  • B23K2103/14—Titanium or alloys thereof
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
  • B23K2103/00—Materials to be soldered, welded or cut
  • B23K2103/18—Dissimilar materials
  • B23K2103/26—Alloys of Nickel and Cobalt and Chromium
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B2250/00—Layers arrangement
  • B32B2250/40—Symmetrical or sandwich layers, e.g. ABA, ABCBA, ABCCBA
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B2305/00—Condition, form or state of the layers or laminate
  • B32B2305/02—Cellular or porous
  • B32B2305/024—Honeycomb
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B2307/00—Properties of the layers or laminate
  • B32B2307/10—Properties of the layers or laminate having particular acoustical properties
  • B32B2307/102—Insulating
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B2311/00—Metals, their alloys or their compounds
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B2605/00—Vehicles
  • B32B2605/18—Aircraft
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T29/00—Metal working
  • Y10T29/49—Method of mechanical manufacture
  • Y10T29/4957—Sound device making
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T29/00—Metal working
  • Y10T29/49—Method of mechanical manufacture
  • Y10T29/49616—Structural member making
  • Y10T29/49618—Restoring existing member, e.g., reinforcing, repairing
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T29/00—Metal working
  • Y10T29/49—Method of mechanical manufacture
  • Y10T29/49718—Repairing

Definitions

• the present invention relates to a method of manufacturing an acoustic attenuation panel, in particular for aeronautics, and to a device for implementing such a method.
• acoustic attenuation panels for example in the nacelles of aircraft engines and nacelle elements equipped with such a panel to reduce the noise emissions of jet engines, is known from the state of the art.
• These acoustic attenuation panels generally have a sandwich structure comprising a structuring skin, a honeycomb-like honeycomb structure, and a resistive layer generally formed by perforated acoustic skin.
• the sound attenuation panels must be designed to be installed in the hot zone of the aircraft turbojet engine nacelle, and in particular in the downstream part of this nacelle through which exhaust gases whose temperature is typically greater than 600 ° C.
• acoustic attenuation panels are generally used, the structuring skin of which is formed by a metal sheet, the honeycomb structure is metallic, and the resistive layer is a perforated metal sheet.
• the cellular honeycomb structure is then bonded by soldering (that is to say by assembling two materials using a filler metal having a melting temperature lower than that of the base metal) to the metal sheet. structure and perforated metal sheet.
• Another possible deterioration of such a panel that must be repaired is the deterioration of the interface interfaces between the structuring skin, the resistive layer and the honeycomb structure affecting the structural qualities of the panel.
• repair methods are known in which all or part of a skin of the acoustic panel and / or of the honeycomb structure is replaced.
• the associated assembly or repair operations are delicate insofar as there is a risk that the acoustic and structural qualities of the panel are affected by these operations such as an allocation of the mechanical strength of the sandwich panel or even a loss of acoustic absorption of the panel.
• assembly or repair operations such as welding or brazing affect the metallurgical properties of the treated board and affect the surface properties of the treated board.
• Defects such as oxidation or the appearance of cracks can result from repair operations.
• An object of the present invention is to overcome the disadvantages mentioned.
• the object of the present invention is therefore notably to provide a method of repairing an acoustic attenuation panel adapted to be installed in a hot zone which eliminates the risk of separation of the skins of the panel with respect to the honeycomb structure of this panel. latest.
• Another object of the present invention is to provide a method of repairing an acoustic attenuation panel adapted to be installed in a hot zone in which the protection against contamination of the treated panel is optimal.
• Another object of the present invention is to provide a method of repairing an acoustic attenuation panel adapted to be installed in a hot zone that meets the requirements relating to the conservation of the acoustic and structural qualities of the repaired panel.
• Another object of the present invention is to provide a method of repairing an acoustic attenuation panel adapted to be installed in a hot zone at lower cost and simple implementation.
• Another object of the present invention is to propose an alternative solution to gaseous protection devices for implementing the aforementioned repair methods.
• the invention proposes a method for repairing an acoustic attenuation panel comprising a structuring skin made of metallic material, a resistive layer made of metallic material and a cellular structure as an acoustic absorption material directly attached to the structuring skin. and the remarkable resistive layer in that it comprises at least one step in which at least one reinforcing pin is inserted into the thickness of said panel and said pin is fixed respectively on the structuring skin and the resistive layer.
• the reinforcing pin is inserted transversely to the honeycomb structure and oriented perpendicular to the planes of the resistive layer and the structuring skin of the panel; -
• the fixing step of the reinforcement pin is a controlled atmosphere welding step right and upside down welded surfaces;
• an inert gas diffusion device is placed on the resistive layer other than a welding torch and a gas ejection nozzle on the other side the panel on the structuring skin;
• perforations are made on the resistive layer and the structuring skin, these perforations being of shape and dimensions complementary to those of the reinforcing pin;
• a deburring step is performed on the inner and outer faces of the resistive layer and the structuring skin.
• the invention also proposes an acoustic attenuation panel implemented by the above-mentioned repair method.
• the present invention further proposes a gaseous protection device implemented during a controlled atmosphere welding step of an acoustic attenuation panel comprising means for injecting inert gas onto said panel and means for receiving a welding torch remarkable in that the inert gas injection means comprises an inert gas diffuser mounted at the periphery of the receiving means of the welding torch.
• the device is adapted to cooperate with the welding torch and allow welding to the right and upside of the solder surfaces of the panel;
• - Welding torch receiving means comprises a housing adapted to receive the welding torch and allow it to pass through a chamber of the device and the diffuser comprises a ring mounted coaxially with the housing receiving the welding torch;
• - Flasher is configured to ensure a non-turbulent gas inlet on the solder surfaces of the panel;
• the diffuser is adapted to diffuse the gas indirectly on the surfaces to be welded, the ring of the diffuser comprising gas outlets on its periphery directed towards the concavity of the enclosure;
• the device further comprises a grid honeycomb through holes placed facing the surfaces to be welded, in order to achieve the welding through the device.
• FIG. 1 schematically shows in section, an embodiment of an acoustic attenuation panel to be repaired by a method according to an embodiment of the present invention
• FIGS. 2 to 7 illustrate the various consecutive steps of the method for repairing the acoustic attenuation panel of FIG. 1 according to one embodiment of the present invention
• FIG. 8 is a perspective view of a gas-shielding device employing a welding step of the process of FIGS. 1 to 7;
• FIG. 9 is a perspective plunging view of the device of FIG. 8.
• an acoustic attenuation panel 100 adapted to be repaired by a method according to the present invention comprises, on the opposite side to the origin of the sound excitation, a structuring skin 120, formed in sheet.
• a honeycomb honeycomb structure 130 as a sound absorption material, known per se.
• a resistive layer 1 10, formed by a perforated plate or by a grid, or by a combination of these two elements, can be attached to the cellular structure 130, so as to encapsulate it between it and the structuring skin 120.
• the performances are less than
• the cellular structure 130 may be attached to the structuring skin 120 and to the resistive layer 1 10 by a brazing or welding process.
• This acoustic attenuation panel 100 is adapted to be used in a high temperature zone, in particular on an aircraft nacelle (n ota m m e n t d s n o l d z o n e d e n d e g d e d e d p e n t e d turbojet engine).
• the structuring skin 120 and the resistive layer 1 can be formed from metallic materials.
• These materials may be selected from metals and / or metal alloys such as titanium, inconel and all their shades.
• the honeycomb structure 130 may be formed, as for el, metal materials, polymers, ceramics or composites, available on the market.
• the material of the honeycomb structure 130 can withstand temperatures of up to 800 ° vs.
• Such a damaged sound attenuation panel 100 may be repaired by a method 200 whose implementation is carried out as follows.
• This panel 100 may be damaged in various ways, namely, according to non-limiting examples, by abrasion, erosion, impact or corrosion.
• the repair method comprises a series of successive steps which will be described in connection with FIGS. 2 to 7.
• perforations 1 1 3 are made on the resistive layer 1 10 with a suitable tooling.
• the position of these perforations 13 may be determined according to the sections of sound attenuation panel 100 which are damaged.
• the positions of these perforations 13 may thus be in non-limiting examples, determined after non-destructive testing (Taptest type, X-ray radiography, ultrasonic testing, etc.) to identify the unbrazed zones. or having another defect.
• These perforations have dimensions and, in particular, a larger diameter than the perforations 1 13 of the resistive layer 1 10.
• This diameter is a function of a deburring tool used in a subsequent process step which will be described with reference to FIG.
• the acoustic attenuation panel 100 is pierced on either side of the cellular structure 130.
• an alternative embodiment provides a suitable drilling device comprising at least one drill whose shape and dimensions are adapted to the perforations 1 13,123 desired.
• This drill can be associated with a support 1 0 ensuring its stability, namely a support 10 tripod type comprising a suitable drilling barrel.
• any excess material present on the structuring skin 1 20 and the resistive layer 1 1 0 to the right perforations 1 13,123 made is removed.
• This excess material may correspond, in particular, to burrs related to the welding or brazing of the structuring skin 1 20 and the resistive layer 1 1 0 with the honeycomb structure 1 30 but also the burrs related to perforations 1 13,123 just made.
• This deburring can be performed by any known deburring technique.
• this deburring makes it possible to avoid any pollution during the welding of subsequent reinforcing pins: thus avoiding, as non-limiting examples, inclusions, lack of bonds, porosities, cracks.
• This tool takes the form of a reamer 20 extended at its free end by a guide 21.
• This guide 21 has an end 22 in the form of a truncated cone of shape and dimensions adapted to pass through the perforations made in the resistive layer 1 10.
• the reamer 20 has, itself, a shape and dimensions identical to that of connecting pins intended to be inserted into the thickness of the panel 100 to the right of the perforations 1 13,123 as will be seen later in relationship with Figure 4.
• reinforcing pins 30 are inserted into the thickness of the acoustic attenuation panel 100, these reinforcing pins 30 extending in contact with the resistive layer 1 1 0 and the structuring skin 120 and more particularly, each reinforcing pin 30 being inserted into the spaces left free by the perforations 1 13, 123 of the resistive layer 1 10 and the structuring skin 120.
• These reinforcing pins are intended to reinforce the interfaces of the cellular structure 130 with, respectively, the resistive layer 1 10 and the structuring skin 120.
• these reinforcement pins 30 extend transversely to the honeycomb structure 130 and are oriented perpendicular to the planes of the resistive layer 1 10 and the structuring skin 120 of the panel 100.
• these reinforcing pins 30 are made of metallic material.
• They may also be of a material similar to that constituting the structuring skin 120 and the resistive layer 1 10.
• each of the reinforcing pins 30 is fixed respectively and successively on the resistive layer 1 and the structuring skin 120 of the panel 100.
• This fixing step 204 may be performed by any known welding or soldering method, offering the advantage of ensuring a continuous connection between each pin 30 and the constituent skins of the panel 100.
• each reinforcement pin 30 is carried out on the resistive layer 1 and the structuring skin 120 of the panel 100 by a method of arc welding with a non-electrode.
• TIG welding type fuse the filler wire being illustrated by the reference 41 in Figure 5b.
• Non-limiting examples of the method include laser welding or resistance welding.
• the fixing step 204 is performed under a controlled atmosphere at the right and upside down welded surfaces.
• an inert gas diffusion device 50 of laggard type for gaseous protection is placed in line with the pins 30 on the side of the external face 1 1 1 from there resistive layer 1 10.
• the gas is an Argon, Helium or a mixture of both.
• This device 50 is adapted to cooperate with the welding torch 40 and allow welding right and upside welded surfaces.
• Such an inert gas diffusion device 50 makes it possible to maintain the weld bead and the heat-affected zone welds between each pin 30 and the skins constituting the panel 100 under an inert atmosphere sufficient to avoid in particular the appearance of cracks.
• This device 50 comprises, more specifically, a local diffusion enclosure 52 equipped with fluid injection means 53 on the treated panel 100.
• This chamber 52 concentrates the diffusion of gas in an inert chamber located on the perforations 1 13 of the resistive layer 1 1 0 wider than that offered by the nozzle associated with the welding torch 40, this in order to avoid the appearance of creeks.
• This enclosure 52 may be flexible and thus able to adapt at least in part to the surface of the treated panel.
• the enclosure 50 comprises a housing adapted to receive the welding torch 40 and allow it to pass through the enclosure 50, in order to approach the welding torch 40 of the zone to be welded.
• This housing is formed by a central orifice 51 through.
• This central orifice may be in the form of a tube, as in FIGS. 8 and 9, or in the form of a cone as in FIGS. 5a and 5b. Any form of orifice may be adapted without departing from the scope of the present invention.
• the gas injection means 53 comprise, for their part, a supply end disposed outside the enclosure 52 and a gas distribution end housed inside the enclosure 52.
• injection means 53 comprise, at their dispensing end, a diffuser 54 housed inside the enclosure 52, that is to say an element intended to be dispersed and spread through the enclosure 52 the unidirectional flow of incoming gas.
• this diffuser 54 is a diffuser mounted on the periphery of the housing of the welding torch 40, configured to ensure a non-turbulent gas inlet, that is to say a laminar diffusion of the latter, on the weld bead each pin 30 and the constituent skin of the corresponding panel 100.
• mounting on the periphery means, in particular, that the diffuser 54 extends at least over a portion of the periphery of the walls of the central orifice 51 forming the housing of the welding torch 40 or all around said periphery, as illustrated in particular in Figures 8 and 9.
• such a device 50 makes it possible to overcome the existing stretches of the above-mentioned methods which are necessarily implemented behind the welding torch to ensure such a laminar diffusion of the gas.
• the diffuser 54 is adapted to diffuse the gas indirectly on the parts to be welded.
• This diffuser comprises a ring 541 mounted coaxially with the central orifice 51 receiving the welding torch 40, this ring 541 comprises gas outlet orifices 542 on its periphery directed towards the concavity of the enclosure, the opposite parts to be welded. With such orifices 542, the diffusion of inert gas is not directed towards the orifices of the skin of the panel 100 but on the opposite, allowing a laminar diffusion of the gas in the enclosure 50.
• the device comprises a grid 543 formed by a honeycomb with through holes placed opposite the parts to be welded, in order to perform the welding through the device.
• the injection nozzle 60 of inert gas placed on the side of the structuring skin 120 it is also adapted to act by pressure on the reinforcement pins 30 when they are fastened to the resistive layer 1 10.
• an inert gas flows on either side of the weld but also in the cellular structure 130, on the inner and outer faces of the resistive layer 1 and the structuring skin 120, thus advantageously limiting any occurrence of solder or solder cracks.
• the atmosphere in which the welding takes place is controlled and problems related to the contamination of the repaired panel 100 can be solved.
• sealing means 61 may be arranged on the circumference of the enclosure 52, in order to guarantee a certain hermeticity of the enclosure 1 1.
• each reinforcing pin 30 includes a narrowing 31 to a length of the pin 30 corresponding to that of the thickness of the panel 100 so that once the part of the pin 30 has broken, the end of the pin 30 comes opposite the structuring skin 120 in the perforation 123 made.
• the reinforcing pin 30 having dimensions now adapted to those of the panel 1 00 is fixed, in a subsequent step 206, the pin 30 with the structuring skin 120 of the panel 1 00 by a welding process similar to the welding step 204 preceding under protective atmosphere through the establishment of the gas diffusion device 50 disposed on the resistive layer 1 10 of the panel, as shown in Figure 7.
• the method 200 for repairing an acoustic attenuation panel 100 according to the present invention may be terminated by a step 207 in which the welds on the outer faces 11, 121 of the resistive layer 1 and the skin are flared. structuring 120.

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• Soundproofing, Sound Blocking, And Sound Damping (AREA)

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• 2011
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