Classifications

• • C—CHEMISTRY; METALLURGY
  • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
  • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
  • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
  • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
  • C22F1/05—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys of the Al-Si-Mg type, i.e. containing silicon and magnesium in approximately equal proportions
• • C—CHEMISTRY; METALLURGY
  • C21—METALLURGY OF IRON
  • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
  • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
  • C21D9/0006—Details, accessories not peculiar to any of the following furnaces
  • C21D9/0025—Supports; Baskets; Containers; Covers
• • C—CHEMISTRY; METALLURGY
  • C21—METALLURGY OF IRON
  • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
  • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
  • C21D9/22—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for drills; for milling cutters; for machine cutting tools
• • C—CHEMISTRY; METALLURGY
  • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
  • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
  • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
  • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
  • C22F1/053—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
• • C—CHEMISTRY; METALLURGY
  • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
  • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
  • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
  • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
  • C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent

Definitions

• the invention initially relates to a method for the heat treatment of a profile, in particular of an extruded profile for aircraft.
• the invention relates to a device for heat treatment of a profile, in particular an extruded profile for aircraft.
• the invention relates to a profile, msr particular an extruded profile for aircraft.
• Extruded profiles in particular formed with age-hardenable aluminum alloys, are widely used in aircraft construction because of the high mechanical strength required there. Due to the requirement of constant weight reductions, the demands on the static load capacity and other mechanical parameters of the aluminum alloy profiles are constantly increasing.
• the object of the invention is to provide a method and a device for optimizing a number of mechanical parameters of a profile, in particular an extruded profile for aircraft.
• a further object of the invention is to provide a profile, in particular an extruded profile, which has different, respectively optimized mechanical parameters in at least two regions. These mechanical parameters are, in particular, the static strength, the fracture toughness and the corrosion resistance
• the method according to the invention can be used for optimizing different material properties of profiles, in particular extruded profiles for aircraft, which are formed from a continuous aluminum alloy.
• the method can also be used for optimizing profiles which are formed from two or more different aluminum alloys become.
• Such profiles can be produced, for example, by means of a coextrusion process with a pressure which is formed from two different aluminum alloys.
• a first chamber encloses a first region of the profile and a second chamber encloses a second region of the profile, wherein different temperatures can be set in the first and the second chamber, different material properties can be defined in the above Create and optimize areas.
• the profile has at least two formed by a differential heat treatment areas, each with different material properties
• the inventive profile can also be used in applications in which the profile simultaneously different requirements, for example in the form of static strength, the fracture toughness and the corrosion resistance, gepOpen must.
• the profile has in a preferred manner, at least in regions, different, respectively, optimized material properties for itself.
• the profile with an aluminum alloy, in particular. formed with a hardenable AIZnCu alloy is formed with an aluminum alloy, in particular. formed with a hardenable AIZnCu alloy.
• the profile has partially optimized material properties.
• a further preferred embodiment of the invention provides that the profile is formed with at least two different, in particular austenitic aluminum alloys. Due to the additional use of at least two differently composed aluminum alloys to form a profile, in conjunction with the differential heat treatment, regions within the profile may be formed which may be optimized in terms of their material properties such as mechanical strength, fracture toughness or corrosion resistance , even more different from each other.
• aluminum profiles with austenitic aluminum alloys which are used for example as ribs for reinforcement in fuselage cells of aircraft, treat in an advantageous manner.
• the profile is subjected to a suitable heat treatment in accordance with the method according to the invention in order to achieve the high static strength desired in this region, to the detriment of the fracture toughness -and / or to allow corrosion resistance.
• the properties of the aluminum profile desired in the region of the belt of the frame can be set and optimized in a targeted manner, at least within the framework of the alloying technology limits.
• the method according to the invention thus avoids the simple and cost-effective provision of aluminum profiles which have different and normally at least partially mutually exclusive material properties in different areas.
• the use of the method according to the invention allows the use of in particular extruded profiles made of aluminum alloys for applications with a wide variety of material requirements, wherein the profiles can be formed only with a continuous alloy.
• Another example of the advantageous application of the method according to the invention is that of strapping pressure profiles with aluminum alloys which are used in aircraft, for example for fastening seats or rows of seats (seat rails).
• the lower portions of such aluminum profiles serve to form the cabin floor and must therefore have a high static strength, since they are an integral part of the entire fuselage cell statics and must absorb considerable forces.
• the inventive method is not limited to the application in profiles that are formed from a Alurniniumleg réelle throughout.
• the extruded profile for the seat slidges from two different afuminum alloys in an extrusion molding process.
• This. can be done for example by so-called 'Koetfrusionshabilit, - in which a pressure formed from two different Alur ⁇ niumleg isten pressed durclt a nozzle wfrd whose opening geometry corresponds approximately to the cross-sectional geometry of the true profile.
• 'Koetfrusions compiler - in which a pressure formed from two different Alur ⁇ niumleg Sammlungen pressed durclt a nozzle wfrd whose opening geometry corresponds approximately to the cross-sectional geometry of the true profile.
• a hardenable aluminum alloy for the upper part of the seat rail.
• high corrosion resistance and fracture toughness can be used for the lower area.
• a differently composed, hardenable aluminum alloy with high static strength values can be used.
• Fig. 1 is a cross-sectional view through an inventive means of
• FIG. 3 shows an exemplary embodiment of a device for carrying out the method according to the invention
• Fig. 4 is a schematic representation of the production of a profile formed from two different aluminum alloys. 5
• Fig. 1 shows a Queritessdarstelluhg by "one by means of the inventive method differentially heat treated profile 1.
• the profile 1 is in particular a Strangpres.sprofi! for aircraft, which is formed throughout from a hardenable Aluminiumjurnlegiefuhg.
• the aluminum alloy may be formed, for example, from a known Alumtniurn-Zi ⁇ k-copper system.
• the profile 1 is formed in a particularly preferred embodiment of the invention with ejner-AIMgSiCu, an AICuMg or an AlZnMgCu alloy. Further, especially by heat treatment curable, alloying systems can In addition, the profile 1 can also be formed from an at least partial combination of the above-described alloying systems.
• the profile 1 has a first region 2 and a second region 3.
• the first region 2 and the second region 3 are separated by a boundary region 4, which runs approximately parallel to a longitudinal axis 5 in the exemplary embodiment of the profile 1 shown.
• the boundary region 4 runs approximately centrally through the profile 1.
• the boundary region 4 represents a transitional zone in which the various thermal properties of the regions 2, 3 are at least partially merged with one another.
• a sharp separation between regions 2, 3 is The Mate ⁇ aleigenschaften technically and physically not possible.
• any geometric shapes of the regions 2, 3 as well as the course of the boundary region 4 are possible.
• profiles with a different, any cross-sectional geometry areas 2,3 may have different material properties.
• the profile 1 shown in FIG. 1 is used, for example, in aircraft construction as a round bulkhead for reinforcing the fuselage cell structure of the aircraft.
• the profile 1 For connection to the fuselage cell ', the profile 1 has a leg 6 which forms a so-called "external flange". The leg 6 serves for frictional connection with longitudinal stiffeners of the fuselage cell.
• a contact surface 7 is formed to form a so-called “inner belt”. The contact surface 7 is used, among other things, for fastening further components to the aircraft structure in the interior region of the fuselage cell.
• the first area 2 and the second area 3 are each subjected to a different heat treatment according to the invention. Therefore, the profile 1 in the first region 2 in particular has a high corrosion resistance and / or fracture toughness and in the second region 3 preferably has a high static strength.
• the profile 1 according to the invention has regionally-as illustrated by the example of the use of the profile 1 as Rundspant in aircraft - different material properties, such as the -static strength, the fracture toughness and / or corrosion resistance, on.
• This can result in a considerable weight and cost savings, because it is no longer absolutely necessary for the formation of profiles with regions of different material properties to combine them of different materials, in particular of different composition, hardenable aluminum alloys.
• the method can also be used to advantage in profiles formed from different aluminum liners. In this case, due to the various aluminum alloys differences in mechanical parameters of the composite 'profile by means of the inventive differential Terriperatufbehähdlulig can be optimized even more extensive.
• the profile 1 can also have a curved or curved geometric design at least in sections.
• a geometric design is For example, if the profile 1 is to be used as a round bulkhead or the like.
• a substantially rectilinear shape of the profile 1 is required, for example, when used as a seat rail or the like.
• the profile 1 preferably has an open cross-sectional geometry.
• An open cross-sectional geometry in this context means a profile 1 with a cross-sectional area that is not enclosed on all sides.
• FIG. 2 shows a time-temperature diagram which schematically illustrates the sequence of the method according to the invention for different or differential heat treatment of the first and second regions 2, 3 of the profile 1 in accordance with an exemplary embodiment. Also in this embodiment, it is assumed that the profile 1 is formed from a continuous, hardenable aluminum alloy.
• the ordinate of the diagram shows the temperature applied to the respective region 2, 3 of the profile, while the abscissa shows the time.
• a erster- temperature curve 8 over time represents the exemplary course of the effect of temperature in the course of differential heat treatment of the invention in the first area 2.
• a with a dotted line shown second 'Temperaturverla ⁇ f 9 represented according to the time course of the effect of temperature in the second region 3.
• the different heat treatments occur simultaneously in the illustrated embodiment of FIG. 2, but can also be performed with a time delay. Basically, it should be noted that exposure to higher temperature for a longer time usually improves the corrosion resistance and / or the cracking ability of the area in question, which increase is generally accompanied by a deterioration in static strength
• both the first area 2 and the second area: 3 are first applied to a pretreatment temperature 1-2.
• the pretreatment phases 10, 11 differ in terms of their duration. In the illustrated method example of FIG. 2 is the second pretreatment phase 11 longer than the first pretreatment phase 10.
• the temperature curves are 8.9 in the region of the pretreatment phases 10.1 1 only slightly outlined for reasons of better graphical representability in the direction of the temperature axis to each other.
• the pretreatment temperature 10 is approximately the same for each of the regions 2, 3.
• the Voranthancilungsphasen 10,11 are used in particular to bring the strength of the entire profile 1, regardless of the areas 2,3, initially to an alloying technology-related maximum value. Notwithstanding the method example shown in FIG. 2, a different pretreatment temperature 12 for the same or different duration of the pretreatment phases 10, 11 can also be selected for the first and second regions 2, 3. This procedure is advantageous, for example, if the profile is formed from two differently composed aluminum alloys. In a particularly preferred way, in profiles, which are formed of a continuous aluminum alloy, the first and second regions 2,3 during the pretreatment stages 10,11 and the so-called pre-storage of a pre-treatment temperature 12 in the range of about 120 0 C and 393 K exposed. In the case of profiles which are formed from at least two different aluminum alloys, deviating values may be required depending on the alloy system used, which may under certain circumstances also vary in certain regions.
• the regions 2, 3 are each exposed to different temperature distributions 8, 9!
• the first region is exposed to a first temperature 14.
• the second region 3 is acted upon by a second temperature 16 during a second exposure time 15.
• Erfindungsg is econceß hiejbei the first Temp ⁇ erature 14 is higher than the second temperature 16 and the first exposure time 13 longer than the second Einwirk- däuer 15th
• a value in the range of approximately 8 to 12 hours is selected for the first exposure time 13.
• a value in the range of about 5 to 8 hours is used.
• the first temperature 14 in this case amounts to approximately 170 ° C. or 443 ° K. while for the second temperature 16 a value of approximately 150 ° C. or 423 ° K. is selected.
• profiles which are formed from two or even a larger number of different aluminum alloys may also be heat-treated differently.
• each of the regions formed from the same aluminum alloy will preferably also be subjected to the same temperature treatment or heat treatment subjected to the same Temperaturverfauf.
• the temperature ranges and exposure intervals already mentioned above may need to be varied depending on the different pinning systems used.
• the use of differently composed Aluminiumlegieionne for the formation of the profile 1 allows a more differentiated development of different material properties, in particular in the form of static strength, the cracking rate and the corrosion rate in each case different sections of the profile.
• FIG. 3 illustrates an exemplary embodiment of a device for carrying out the method according to the invention on the profile 1 with the first region 2 and the second region 3.
• the first region 2 is surrounded by a first chamber 17 closed on all sides and the second region 3 is surrounded by a second chamber 18 closed on all sides.
• the chambers 17, 18 can be formed, for example, by elongate, longitudinally slotted tubular structures, in particular in the form of heat-resistant tubes 19, 20 or the like.
• the tubes 19, 20 are pushed or pressed onto the corresponding regions 2, 3 of the profile 1 for this purpose after introduction of a corresponding longitudinal slot along the longitudinal axis 5 and / or in the direction of a transverse axis 21.
• longitudinal edges 23 of the tubes 19, 20 approximately contact one another or the profile 1 and seal the chambers 17, 18 almost completely against one another.
• a first temperature 24 and in the second chamber 18, a second temperature 25 can be set or maintained.
• the temperatures 24, 25 are preferably set differently. Possible thermal compensations between the first region 2 and the second region 3 as a result of leaks in the boundary region 22 and / or due to possible heat conduction processes between the regions 2, 3 of the profile 1 are at the prevailing temperature difference generally negligible.
• the chambers 17,18 are especially liquid and / or gaseous media, such as hot air.
• The. Generation of the hot air takes place here with a device not shown, beispielswei- se with an electrically heated hot air blower or the like.
• temperature sensors are arranged inside the chambers 17, 18 in order to keep the temperatures 24, 25 within the chambers 17, 18 as close as possible to the values predetermined by the temperature profiles 8, 9 by means of a control and regulating device.
• the control and regulating device may in this case be designed, for example, in the form of a known computer unit.
• sealing means can be provided in order to further improve the seal between the first chamber 17 and the second chamber 18 and the profit 1.
• the sealants may, for example, in the
• Form of sealing lips be formed by Abflachu ⁇ gen the tubes
• the profile 1 remains within the device in accordance with the predetermined temporal temperature curves 8,9 a total of up to 12 hours plus the duration of the pretreatment phases 10,11.
• the tubes 19, 20 can be connected to each other along the longitudinal edges 23, in each case below or above the profile 1.
• the tubes 19,20 in the area of longitudinal edges exteriors are separable "and formed resealable, 'most to the applicability to the profile 1 zu.ge Theoryrlei.
• FIG. 4 shows an exemplary embodiment of a profile 26 which is formed from a first and a second alloy region 27, 28, wherein the alloy regions 27, 28 are each formed from differently composed hardenable aluminum alloys.
• the alloy regions 27, 28 abut one another in a boundary region 29.
• a mixing of the two alloys takes place, at least in some areas, so that in this region at least one partial mixing of the material properties.
• the boundary region 29 runs approximately parallel to a longitudinal axis 30
• a cylindrical pressure 31 shown in the exemplary embodiment shown is pressed under high pressure in the direction of the arrows 32, 33 through a nozzle 34.
• the opening geometry of the nozzle 34 corresponds approximately to the cross-sectional geometry of the profile to be pressed 26.
• the Presshng 31 is formed by stacked half-cylinder 35,36.
• the half cylinders 34, 35 are each formed from differently composed aluminum alloys, that is, the alloy regions 27, 28 each have correspondingly different material properties.
• the material properties mentioned are, in particular, the mechanical strength, the fracture toughness, the corrosion resistance and the thermal availability of the profile 26.
• the material used to form the semicylders 35, 36 is, in particular, hardenable aluminum alloys, for example AIMgSiCu, AICuMg and AIZnMgCu, Systems use.
• the profile 26, for example, by joining already extruded Teiiprofile of different .Aluminiumlegtechniken by means of known joining methods, for example by welding, friction / R ⁇ hrsch Denen or the like are formed.
• the profile 26 * is then subjected to a differential heat treatment in accordance with the method described above or a treatment in the device already explained.
• areas which are formed from the same aluminum alloy are preferably also subjected to the same temperature control.
• the alloy regions 27, 28 simultaneously form a first and a second region 37, 38 that correspond to those regions 2, 3 which, as already described above, according to the invention procedural subjected to a differential heat treatment according to the specifications of the temperature curves 8.9 (see in particular Fig. 1 and 2).
• profiles 1, 26, which are formed of at least two differently composed aluminum alloys, erla.ubt in combination with the method according to the invention or in particular the emergence of locally even more distinctive material properties, as in the use of only an aluminum alloy formed profiles would be the case. Finally, more than two different aluminum alloys can be used to form the profile 26.

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• Chemical & Material Sciences (AREA)
• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• Crystallography & Structural Chemistry (AREA)
• Thermal Sciences (AREA)
• Materials Engineering (AREA)
• Physics & Mathematics (AREA)
• Metallurgy (AREA)
• Organic Chemistry (AREA)
• Extrusion Of Metal (AREA)
• Body Structure For Vehicles (AREA)
• Pressure Welding/Diffusion-Bonding (AREA)
• Forging (AREA)
• Shaping Metal By Deep-Drawing, Or The Like (AREA)

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• 2006
  • 2006-04-13 CN CN2006800541839A patent/CN101415855B/zh not_active Expired - Fee Related
  • 2006-04-13 BR BRPI0621538-6A patent/BRPI0621538A2/pt not_active Application Discontinuation
  • 2006-04-13 US US12/226,231 patent/US8101120B2/en not_active Expired - Fee Related
  • 2006-04-13 CA CA2643824A patent/CA2643824C/en not_active Expired - Fee Related
  • 2006-04-13 EP EP06724329A patent/EP2004871A1/de not_active Withdrawn
  • 2006-04-13 WO PCT/EP2006/003442 patent/WO2007118489A1/de active Application Filing
  • 2006-04-13 JP JP2009504569A patent/JP4815531B2/ja not_active Expired - Fee Related

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