DE102009023059A1 - Repairing a defective surface of an aircraft component, comprises impinging the component with a force in the area of its defective surface using a sonotrode-like hardening tool, which is stimulated in ultrasound frequency range - Google Patents

Repairing a defective surface of an aircraft component, comprises impinging the component with a force in the area of its defective surface using a sonotrode-like hardening tool, which is stimulated in ultrasound frequency range

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Publication number
DE102009023059A1
DE102009023059A1 DE102009023059A DE102009023059A DE102009023059A1 DE 102009023059 A1 DE102009023059 A1 DE 102009023059A1 DE 102009023059 A DE102009023059 A DE 102009023059A DE 102009023059 A DE102009023059 A DE 102009023059A DE 102009023059 A1 DE102009023059 A1 DE 102009023059A1
Authority
DE
Germany
Prior art keywords
component
surface
hardening tool
area
tool
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
DE102009023059A
Other languages
German (de)
Inventor
Joachim Dr. Bamberg
Erwin Dr. Bayer
Roland Dr. Hessert
Jürgen Dr. Steinwandel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
DaimlerChrysler Aerospace AG
MTU Aero Engines GmbH
Original Assignee
MTU Aero Engines GmbH
EADS Deutschland GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines GmbH, EADS Deutschland GmbH filed Critical MTU Aero Engines GmbH
Priority to DE102009023059A priority Critical patent/DE102009023059A1/en
Publication of DE102009023059A1 publication Critical patent/DE102009023059A1/en
Application status is Pending legal-status Critical

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23POTHER WORKING OF METAL; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00Restoring or reconditioning objects
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64FGROUND 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
    • B64F5/00Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/40Maintaining or repairing aircraft

Abstract

The method for repairing a defective surface (12a) of an aircraft component (10), comprises impinging the component with a force in the area of its defective surface using a sonotrode-like hardening tool (14), which is stimulated in ultrasound frequency range. The component and the hardening tool are manually and/or mechanically guidably moved relative to each other. The hardening tool is used with a stamp-like armored hardening tool head (20), and is aligned opposite to the surface of the component, so that a hardening tool axis runs in an operating direction of the hardening tool. The method for repairing a defective surface (12a) of an aircraft component (10), comprises impinging the component with a force in the area of its defective surface using a sonotrode-like hardening tool (14), which is stimulated in ultrasound frequency range. The component and the hardening tool are manually and/or mechanically guidably moved relative to each other. The hardening tool is used with a stamp-like armored hardening tool head (20), and is aligned opposite to the surface of the component, so that a hardening tool axis running in an operating direction of the hardening tool is arranged parallelly and/or at angle of 10-80[deg] to a surface normal of the surface in the impingement area. The component is held by a holding device, and is held by applying a low pressure to the holding device. The component is impinged in the area of several defective surfaces and/or is multiply impinged in the area of the defective surface and/or multiply impinged with different angles between the surface normal of the surface in the impingement area and the hardening tool axis of the hardening tool. The component is repaired with crack, crack growth, material inhomogeneity, scratch and/or depression as defective surface, where a thin-walled component is repaired in the area of the defective surface. An independent claim is included for a device for repairing a defective surface of an aircraft component.

Description

  • The The invention relates to a method and a device for repairing a faulty surface of a component, in particular an aircraft component.
  • One Such a method and such a device are already known from the prior art and serve to avoid Cracks and cracks resulting from a scratch, a material inhomogeneity, a depression or other error of a surface a component, in particular an aircraft component, can go out. This problem occurs in particular for components that at least in the area of the surface defect comparatively thin-walled are formed. In a known method for repairing the faulty surface becomes the faulty surface area cut out and welded a new molding.
  • This However, the process is very time consuming and labor intensive, thereby high repair costs arise. Additionally need in this method optionally existing backings of the component are removed, which causes a further increase the repair costs.
  • alternative it is known, the component at least in the area of its surface defect to apply a force to repair the component and to prevent a progression of the surface defect. The application of force takes place by deep rolling the damaged Surface area, causing local compressive stresses in the Component are generated.
  • Also however, this process is relatively time consuming and labor intensive. In addition, the process can not with thin-walled components performed without support of the component which leads to considerable problems and cost increases if the component is accessible only from one side.
  • task It is the object of the present invention to provide a method and an apparatus of the type mentioned above, which provide a faster and less expensive repair of a faulty surface allow a component.
  • The The object is achieved by a method with the features of claim 1 and by a device solved with the features of claim 13. advantageous Embodiments of the invention are in the subclaims given, wherein advantageous embodiments of the method as advantageous embodiments of the device are to be considered.
  • In a method according to the invention for repairing a faulty surface of a component, in particular of an aircraft component, the surface of the component is acted upon at least in the region of the faulty surface by means of at least one sonotrode-like solidification tool, which is excited in the ultrasonic frequency range. In other words, it is provided that in the area of the faulty surface local, deep-reaching compressive stresses are generated by means of the so-called Ultrasonic Impact Treatment (UIT). Although the application of UIT process in the component reworking example of the DE 10 2004 058 146 A1 basically known. The Applicants have recognized, however, that the method is surprisingly suitable for the repair of defective and damaged surfaces of components and allows various advantages. With the help of sonotrodenartigen hardening tool whose excitation energy is transferred to the faulty surface of the component and solidifies it. The component can be repaired quickly and economically, and errors can be easily repaired even if the faulty surface is accessible only on one side. Cracking or crack growth is effectively suppressed by solidification of the component material, reliably avoiding unwanted deformations. It is irrelevant whether the surface of the component is flat or curved, it being possible for the hardening tool to have a contour or geometry adapted to the surface. The method is also suitable for repairing high-stress surfaces such as edges, welds or holes. The process can also be carried out without infrastructure and increased tooling and is thus applicable, for example, at each airport.
  • In an advantageous embodiment of the invention is provided that the component and the solidification tool manually and / or be guided mechanically guided relative to each other. This can the faulty surface repaired specifically and individually become. It can be provided that the component is fixed in position and the solidification tool is moved, that the solidification tool is stationary and the component is moved or that both the component as well as the solidification tool are moved relative to each other. The movement can be done manually, d. H. hand-guided, or by machine, z. B. by means of a robot, are carried out so that a particularly flexible implementation of the repair process is possible.
  • In a further advantageous embodiment of the invention, it is provided that the hardening tool in such a way with respect to the surface is aligned to the component, that in the effective direction of the solidification tool extending solidification tool axis is arranged parallel and / or at an angle, in particular at an angle between 10 ° and 80 °, to a surface normal of the surface in the loading area. In this way, a further advantageous adaptability to different types of components, surface geometries and types of errors is given, as can be realized by setting the effective direction targeted preferential solidification states in the surface.
  • Further Advantages arise by the fact that the component by means of a holding device is held. As a result, a reliable position fixation allows the component, creating a correspondingly precise Repair of faulty surface feasible is.
  • By doing as a holding device, a cross table is used, the component very precise in two spatial directions within one Plane to be moved, leaving a defined work space and Travel path results. It can be provided that a cross table with adjustable angular offset between the spatial directions (so-called. Swing table) is used to another degree of freedom in the Allow movement of the component.
  • A unwanted damage of the component is in further embodiment ensures that the component held by applying a negative pressure to the holding device becomes. This also allows components with complex geometries quick, easy and gentle to the holding device solvable be determined.
  • A particularly reliable and individualized to the respective Error-adjustable repair is in a further refinement allows the component to be in the range of several faulty Surfaces and / or multiply in the range of at least one faulty surface and / or multiple with different Angles between the surface normal of the surface in the loading area and the solidifying tool axis of the Festfestigungswerkzeugs is applied.
  • In a further advantageous embodiment of the invention is provided a component with a crack and / or a crack progress and / or a material inhomogeneity and / or a scratch and / or a depression repaired as a faulty surface becomes. This can cause a variety of surface defects as well as different, in different areas or from different ones Reasons faulty components under the realization of the above Advantages to be repaired.
  • In a further advantageous embodiment of the invention is provided that at least in the area of the faulty upper surface thin-walled component is repaired. When high-frequency Applying force with the help of the sonotrode-like hardening tool also have thin-walled components enough inert mass, without back support and without macroscopic Deformation solidifies and thus fast, easy and inexpensive to be repaired.
  • Further Benefits arise when a solidification tool with a armored consolidation tool head is used. This allows almost independent of the material of the component a particular efficient power transmission from the solidification tool on the surface of the component and an associated high plastic deformation of the component material. Continue As a result, the durability of the solidification tool or his Hardening tool head advantageous increased.
  • there Is provided in a further embodiment of the invention that a Solidifying tool head is used, which at least partially Tungsten carbide and / or titanium nitride and / or boron nitride. hereby Can be a very high hardness and wear resistance of the solidifying tool head.
  • Around repair different surface geometries easily it has also proven to be advantageous when a consolidation tool with a stamped solidification tool head is used. This can be done in a structurally simple way and regardless of the surface geometry a punctual Compaction of the component material and thus a particularly deep-reaching Compressive stress can be generated.
  • Another aspect of the invention relates to a device for repairing a faulty surface of a component, in particular an aircraft component, wherein according to the invention a faster and cheaper repair of a faulty surface of a component is made possible by the fact that the device comprises at least one sonotrodenartiges solidification tool, which is excitable in the ultrasonic frequency range and by means of which the surface of the component can be acted upon at least in the region of the defective surface. As a result, with the aid of the hardening tool, in contrast to the prior art, local, deep-reaching compressive stresses can be generated in the component and the faulty surface can be repaired. In the case of high-frequency impact treatment (Ultrasonic Impact Treatment (UIT)), even thin-walled component structures have enough inertial mass to be able to do so without back support and without macroscopic deformation can be solidified. The embodiments and developments described above in connection with the method according to the invention and their advantages apply correspondingly to the device according to the invention.
  • Further Features of the invention will become apparent from the claims, the embodiment and the drawing. The above features and feature combinations mentioned in the description and those mentioned below in the exemplary embodiment Features and feature combinations are not just in each case specified combination, but also in other combinations or usable in isolation, without departing from the scope of the invention. The single figure shows a perspective schematic representation a component with a faulty surface, which repaired by means of a sonotrode-like solidification tool becomes.
  • The single figure shows a perspective schematic representation of a component 10 with a faulty surface 12a , which by means of a sonotrodenartigen hardening tool 14 is repaired. For repairing the component 10 , which in the present case is designed as a housing component of an aircraft, becomes its surface 12 at least in the area of the faulty surface 12a by means of the hardening tool 14 applied, causing a plastic deformation of the component 10 and local compressive stresses in the component 10 be generated. The hardening tool 14 is excited in the ultrasonic frequency range, resulting in a so-called ultrasonic impact treatment (UIT) of the component 10 he gives. The component 10 has a scratch as a surface defect 12a on. The repair reliably avoids crack initiation or crack propagation from the scratch. Alternatively or additionally, however, other surface defects can also be used 12a such as local material inhomogeneities, unfavorable stress conditions in joint joints, cracks, depressions, or the like can be repaired to prevent crack propagation.
  • The component 10 is present thin-walled and includes on its faulty surface 12a facing away from a back feeding 16 , whereby the component 10 accessible only from one side. Unlike the prior art, the backfilling needs 16 but not dismantled to carry out the repair process. In addition, the thin-walled component has 10 by the high-frequency application of force (hammering) with the hardening tool 14 sufficient inertial mass to be solidified without back support and without macroscopic deformation. As a result, the repair can be carried out particularly quickly and economically.
  • The hardening tool 14 , the basic structure of which is known from the prior art, in turn comprises an actuator 18 which is a stamped solidification tool head 20 vibrated in the ultrasonic frequency range. The hardening tool head 20 , which is formed armored and serving at its end serving for loading z. B. a tungsten carbide hemisphere 22 in turn, transmits the vibrational energy to the surface 12 or on the faulty surface area 12a , whereby the component 10 is solidified at the impacted point. An effective direction of the solidification tool 14 extending solidification tool axis A in the present example is parallel to a surface normal of the surface 12 arranged in the loading area. Alternatively or additionally, the solidification tool axis A at an angle, in particular at an angle between 10 ° and 80 °, to Flächennor paint the surface 12 be arranged in the loading area in order to achieve preferred oriented solidification conditions.
  • The component 10 and the solidification tool 14 are moved manually and / or mechanically guided relative to each other during the repair. In the present embodiment, the component remains 10 stationary while the solidification tool 14 is moved in accordance with the arrows I, II. This allows a repair of the component 10 without it having to be removed. However, it can also be provided that the component 10 by means of a holding device (not shown) is held. As a holding device, for example, a cross table can be used. Likewise, it can be provided that the component is held by applying a negative pressure to the holding device.
  • In summary, the method allows a quick and economical repair of scratches or other surface defects 12a especially on thin-walled components 10 and can be easily done even if the surface 12 accessible only from one side. Any crack growth is effectively suppressed by solidification of the component material without causing macroscopic deformations of the component 10 would come. The procedure is applicable locally and without infrastructure overhead, for example directly at an airport.
  • QUOTES INCLUDE IN THE DESCRIPTION
  • This list The documents listed by the applicant have been automated generated and is solely for better information recorded by the reader. The list is not part of the German Patent or utility model application. The DPMA takes over no liability for any errors or omissions.
  • Cited patent literature
    • DE 102004058146 A1 [0008]

Claims (13)

  1. Method for repairing a faulty surface ( 12a ) of a component ( 10 ), in particular an aircraft component, in which the component ( 10 ) at least in the area of its faulty surface ( 12a ) is acted upon by a force, characterized in that the surface ( 12 ) of the component ( 10 ) at least in the area of the defective surface ( 12a ) by means of at least one sonotrode-like solidification tool ( 14 ), which is excited in the ultrasonic frequency range, is applied.
  2. Method according to claim 1, characterized in that the component ( 10 ) and the solidification tool ( 14 ) are moved manually and / or mechanically guided relative to each other.
  3. Method according to claim 1 or 2, characterized in that the hardening tool ( 14 ) in such a way opposite the surface ( 12 ) of the component ( 10 ), that one in the direction of action of the solidification tool ( 14 ) solidifying tool axis (A) parallel and / or at an angle, in particular at an angle between 10 ° and 80 °, to a surface normal of the surface ( 12 ) is arranged in the loading area.
  4. Method according to one of claims 1 to 3, characterized in that the component ( 10 ) is held by means of a holding device.
  5. Method according to claim 4, characterized in that in that a cross table is used as the holding device.
  6. Method according to claim 4 or 5, characterized in that the component ( 10 ) is held by applying a negative pressure to the holding device.
  7. Method according to one of claims 1 to 6, characterized in that the component ( 10 ) in the area of several defective surfaces ( 12a ) and / or several times in the area of at least one faulty surface ( 12a ) and / or several times with different angles between the surface normal of the surface ( 12 ) in the loading area and the solidifying tool axis (A) of the solidifying tool ( 14 ) is applied.
  8. Method according to one of claims 1 to 7, characterized in that a component ( 10 ) with a crack and / or a crack progress and / or a material inhomogeneity and / or a scratch and / or a depression as a faulty surface ( 12a ) is repaired.
  9. Method according to one of claims 1 to 8, characterized in that at least in the region of the faulty surface ( 12a ) thin-walled component ( 10 ) is repaired.
  10. Method according to one of claims 1 to 9, characterized in that a hardening tool ( 14 ) with an armored consolidation tool head ( 20 ) is used.
  11. Method according to claim 10, characterized in that a hardening tool head ( 20 ) which is at least partially composed of tungsten carbide ( 22 ) and / or titanium nitride and / or boron nitride.
  12. Method according to one of claims 1 to 11, characterized in that a hardening tool ( 14 ) with a stamp-like solidification tool head ( 20 ) is used.
  13. Device for repairing a faulty surface ( 12a ) of a component ( 10 ), in particular of an aircraft component, characterized in that the device comprises at least one sonotrode-type hardening tool ( 14 ), which is excitable in the ultrasonic frequency range and by means of which the surface ( 12 ) of the component ( 10 ) at least in the area of the defective surface ( 12a ) can be acted upon.
DE102009023059A 2009-05-28 2009-05-28 Repairing a defective surface of an aircraft component, comprises impinging the component with a force in the area of its defective surface using a sonotrode-like hardening tool, which is stimulated in ultrasound frequency range Pending DE102009023059A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE102009023059A DE102009023059A1 (en) 2009-05-28 2009-05-28 Repairing a defective surface of an aircraft component, comprises impinging the component with a force in the area of its defective surface using a sonotrode-like hardening tool, which is stimulated in ultrasound frequency range

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102009023059A DE102009023059A1 (en) 2009-05-28 2009-05-28 Repairing a defective surface of an aircraft component, comprises impinging the component with a force in the area of its defective surface using a sonotrode-like hardening tool, which is stimulated in ultrasound frequency range

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DE102009023059A1 true DE102009023059A1 (en) 2010-12-02

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DE102009023059A Pending DE102009023059A1 (en) 2009-05-28 2009-05-28 Repairing a defective surface of an aircraft component, comprises impinging the component with a force in the area of its defective surface using a sonotrode-like hardening tool, which is stimulated in ultrasound frequency range

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2465636A1 (en) * 2010-12-16 2012-06-20 MTU Aero Engines GmbH Method and device for forming a section of a component with a predefined contour

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19809581A1 (en) * 1998-03-06 1999-09-09 Krause Working metal between hammer and support
US6338765B1 (en) * 1998-09-03 2002-01-15 Uit, L.L.C. Ultrasonic impact methods for treatment of welded structures
JP2002210569A (en) * 2001-01-16 2002-07-30 Mishima Daiji Ultrasonic vibrating horn in ultrasonic welding apparatus
DE10243415A1 (en) * 2002-09-18 2004-04-01 Alstom (Switzerland) Ltd. Process for the generation of residual compressive stresses in the surface of workpieces
DE102004058146A1 (en) 2004-12-02 2006-06-08 Mtu Aero Engines Gmbh Method and device for surface hardening of components

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19809581A1 (en) * 1998-03-06 1999-09-09 Krause Working metal between hammer and support
US6338765B1 (en) * 1998-09-03 2002-01-15 Uit, L.L.C. Ultrasonic impact methods for treatment of welded structures
US7344609B2 (en) * 1998-09-03 2008-03-18 U.I.T., L.L.C. Ultrasonic impact methods for treatment of welded structures
JP2002210569A (en) * 2001-01-16 2002-07-30 Mishima Daiji Ultrasonic vibrating horn in ultrasonic welding apparatus
DE10243415A1 (en) * 2002-09-18 2004-04-01 Alstom (Switzerland) Ltd. Process for the generation of residual compressive stresses in the surface of workpieces
DE102004058146A1 (en) 2004-12-02 2006-06-08 Mtu Aero Engines Gmbh Method and device for surface hardening of components

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2465636A1 (en) * 2010-12-16 2012-06-20 MTU Aero Engines GmbH Method and device for forming a section of a component with a predefined contour

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