CN100339501C - Aluminum-zinc-magnesium-copper alloy extrusion - Google Patents
Aluminum-zinc-magnesium-copper alloy extrusion Download PDFInfo
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- CN100339501C CN100339501C CNB038244020A CN03824402A CN100339501C CN 100339501 C CN100339501 C CN 100339501C CN B038244020 A CNB038244020 A CN B038244020A CN 03824402 A CN03824402 A CN 03824402A CN 100339501 C CN100339501 C CN 100339501C
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/10—Alloys based on aluminium with zinc as the next major constituent
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- 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
Abstract
An aluminum alloy extrusion product having improved strength and fracture toughness, the aluminum base alloy comprised of 1.95 to 2.5 wt.% Cu, 1.9 to 2.5 wt.% Mg, 8.2 to 10 wt.% Zn, 0.05 to 0.25 wt.% Zr, max. 0.15 wt.% Si, max. 0.15 wt. % Fe, max. 0.1 wt. % Mn, the remainder aluminum and incidental elements and impurities.
Description
The present invention relates to the Al-Zn-Mg-Cu alloy and relate more specifically to be used for the Al-Zn-Mg-Cu squeezing prod of aircraft application and make the method for this squeezing prod.In addition, the present invention relates to have the Al-Zn-Mg-Cu alloy extrusion of improved fracture toughness.
Existing Al-Zn-Mg-Cu alloy may have relative high intensity under moderate erosion resistance and moderate destruction tolerance limit or fracture toughness property.The such alloy and the method for obtained performance will be described in (following) patent.For example, United States Patent (USP) 4,863,528 disclose method of producing aluminium alloy and the finished product with the combination of improved strength and erosion resistance.This method comprises provides the alloy of being made up of following ingredients basically: about 6-16% zinc, about 1.5-4.5% magnesium, about 1-3% copper, selected among zirconium, chromium, manganese, titanium, it is about 1% that one or more elements of vanadium and hafnium, the total amount of described element are no more than, the aluminium of surplus and incidental impurity.Then this alloy is carried out solution heat treatment, precipitation hardening so as with its intensity bring up to than solution heat treatment strength level exceed this solution heat treatment strength level and maximum strength difference at least about 30% level, handle being enough to improve under the temperature of its corrosion resistance, and then carry out precipitation hardening so that improve its yield strength and produce high strength, high erosion-resisting alloy product.
United States Patent (USP) 5,221,377 disclose and have had improved strength, density, the alloy product of toughness and erosion resistance combination, described alloy product is made up of following ingredients basically: about 7.6-8.4% zinc, about 1.8-2.2% magnesium, about 2-2.6% copper and at least a selected among zirconium, the element of vanadium and hafnium, described element to exist total amount to be no more than about 0.5%, preferred about zirconium of 0.05 to 0.25%, the aluminium of surplus and incidental element and impurity.This alloy product that is applicable to aerospace application shows high yield strength, than the corresponding product height of its 7X50-T6 at least about 10% yield strength, and have good toughness and with the quite or better corrosion resistance of its 7X50-T76 corresponding product typical case.The top wing parts typical case who is made by this alloy has the yield strength above 579MPa (84ksi), good fracture toughness property and " EC " or better and be typically the EXCO exfoliation resistance level of " EB ".
United States Patent (USP) 4,477,292 disclose three step thermal life methods of the intensity that is used for improving the product that contains the solution heat treatment aluminium alloy and erosion resistance, and this alloy comprises zinc, magnesium, copper and at least a chromium that is selected from, the element of manganese and zirconium.Under about 79.4-163 ℃ (175 ° to 390 ), this product is carried out precipitation hardening, the thermal treatment several minutes carried out precipitation hardening then once more by several hours under about 79.4-163 ℃ (175 ° to 390 ) under the temperature of about 162-199 ℃ (360 ° to 390 ).In preferred embodiments, the product of processing comprises the aluminium alloy 7075 of T6 state.The method of this invention is easy to control and be applicable to the product that processing is thicker than other comparable method.
United States Patent (USP) 5,108,520 disclose metal alloy have been carried out solution heat treatment, the aging technique of precipitation hardening, this technology comprises at first carries out incomplete timeliness to this alloy, so that obtain to be lower than the yield strength of peak value yield strength, carry out higher timeliness subsequently so that improve the erosion resistance of this alloy, carry out the timeliness of lesser temps subsequently so that intensity is brought up to more than the initial strength.
United States Patent (USP) 5,560,789 disclose AA7000 series alloy with high mechanical strength and the method that obtains them.This alloy comprises 7 to 13.5% weight Zn, 1 to 3.8% weight Mg, 0.6 to 2.7% weight Cu, 0 to 0.5% weight Mn, 0 to 0.4% weight Cr, 0 to 0.2% weight Zr, 0.05% weight and total amount other element of 0.15% weight and the Al of surplus at the most at the most respectively.Can obtain alloy malleable or casting, and this product and DEA melt the specific energy that signal interrelates and are lower than 3J/g.
United States Patent (USP) 5,312,498 disclose the manufacture method of the aluminum base alloy product with improved exfoliation resistance and fracture toughness property, this method comprises provides the aluminum base alloy composition of being made up of following ingredients basically: the zinc of about 5.5-10.0% weight, the magnesium of about 1.75-2.6% weight, the copper of about 1.8-2.75% weight, the aluminium of surplus and other element.This aluminum base alloy is processed, thermal treatment, quenching and timeliness have the corrosion resistance of improvement and the product of mechanical property so that make.Zinc, magnesium and copper have the equilibrated stoichiometry, after the precipitation that produces owing to aging technique is finished substantially, do not have superfluous element like this.The manufacture method of this aluminum base alloy product has been utilized a step or two step ageing treatment and has been combined copper, the stoichiometric balance of magnesium and zinc.
United States Patent (USP) 4,711,762 disclose the aluminum base alloy product of improvement, and this alloy comprises 0 to 3.0% weight Cu, 0 to 1.5% weight Mn, 0.1 to 4.0% weight Mg, 0.8 to 8.5% weight Zn, at least 0.005% weight Sr, 1.0% weight Si at the most, 0.8% weight Fe and 0.45% weight Cr at the most at the most, 0 to 0.2% weight Zr, the aluminium of surplus and subsidiary element and impurity.
United States Patent (USP) 1,418,303 disclose the improved aluminum alloy of being made up of following ingredients: about 0.1% to the copper less than 3% any amount, about 0.1% to about 2% titanium, about 6% to about 16% zinc preferably is no more than 0.6% iron (impurity as commercial aluminium exists), preferably is no more than 0.4% silicon (impurity as commercial aluminium exists), preferably be no more than other element (impurity) of 0.4%, the aluminium of surplus.
United States Patent (USP) 2,290,020 discloses and has contained aluminium, and the improved aluminum alloy of the ternary compound of zinc and magnesium, the scope of the amount of this compound are about 2% to 20%, and preferred range is 3% to 15%.This ternary compound enters sosoloid in the aluminium alloy with about 2% amount under the room temperature.Per-cent under the high temperature in the sosoloid improves and reduces the excess electron excess fraction precipitation during cooling.
United States Patent (USP) 3,637,441 disclose aluminium base sintered alloy product, and this alloy product has the improved combination of high transverse yield strength and high stress-corrosion-cracking resistance.This alloy comprises basic precipitation hardening element zinc, and magnesium and copper add dispersion-strengthened elemental iron and nickel.It also can comprise chromium and/or manganese in addition.By the efflorescence of element melt, hot-work, solution heat treatment is quenched and artificial aging prepares this alloy.The composition of this alloy except that aluminium is, the zinc of at least 6.5 to 13% weight, the magnesium of 1.75 to 6% weight, the copper of 0.25 to 2.5% weight, 0.75 to the iron of 4.25% weight and the nickel of 0.75 to 6% weight, the manganese of 3% weight and the chromium of 0.75% weight at the most at the most.The ratio of iron and nickel is 0.2: 1 to 2.0: 1.
United States Patent (USP) 5,028,393 disclose the Al base alloy as sliding material (sliding), this alloy has good anti-fatigue performance and antistick (seizure) performance and is made up of following ingredients: 1-10% weight Zn, 1-15% weight Si, 0.1-5% weight Cu, 0.1-5% weight Pb, the Al of 0.005-0.5% weight Sr and surplus and incidental impurities.
United States Patent (USP) 6,315,842 disclose by thickness rolling greater than 60mm, the mould that is used for plastic prod that extruding or forging AlZnMgCu alloy product are made, and this alloy comprises following composition (by weight percentage): 5.7＜Zn＜8.7,1.7＜Mg＜2.5,1.2＜Cu＜2.2, Fe＜0.14, Si＜0.11,0.05＜Zr＜0.15, Mn＜0.02, Cr＜0.02, while Cu+Mg＜4.1 and Mg＞Cu, other element every kind＜0.05 and total amount＜0.10, by solution heat treatment, quenching and timeliness to T6 tempering are handled this product.
, yet still there are to having high-caliber intensity erosion resistance, the improved aluminum alloy that is used for aircraft application of fracture toughness property and good antifatigue crack growth performance and the great demand of the squeezing prod of manufacturing thus although existing these are open.The invention provides such squeezing prod.
The purpose of this invention is to provide the improvement Al-Zn-Mg-Cu alloy extrusion that is used for aircraft.
Another object of the present invention provides the fracture toughness property with improvement and has the Al-Zn-Mg-Cu alloy extrusion of high strength level.
Another purpose of the present invention provides has the improved strength performance, the manufacture method of the Al-Zn-Mg-Cu alloy extrusion of fracture toughness property and antifatigue crack growth performance.
Another object of the present invention provides has the improved strength performance, fracture toughness property, the manufacture method of the Al-Zn-Mg-Cu alloy product of good anticorrosive level.
Another object of the present invention provides the aeronautic structure parts, for example the squeezing prod of being made by alloy of the present invention.
According to these purposes, the method of making the aluminium alloy extruded product with improved fracture toughness is provided, this method comprises the following steps: to provide by 1.95 to 2.5% weight Cu, 1.9 to 2.5% weight Mg, 8.2 to 10% weight Zn, 0.05 to 0.25% weight Zr, 0.15% weight Si at the most, 0.15% weight Fe at the most, 0.1% weight Mn at the most, the molten mass of the aluminum base alloy that the aluminium of surplus and subsidiary element and impurity are formed; Cast this aluminium alloy molten mass so that congealed solid is provided, between liquidus line and solidus temperature, make the molten aluminum matrix alloy graining, so that the congealed solid of the grain-size with 25 to 75 mu m ranges is provided with 600 ° of speed of per second to 800 ° of K scopes.By at the first temperature range internal heating of 449-460 ℃ (840 ° to 860 s) subsequently at the second temperature range internal heating of 360-471 ℃ (680 ° to 880 s) this congealed solid carried out homogenizing so that provide have MgZn thereafter,
2Or the sedimentary equally distributed homogeneous mass of η.Then this homogeneous mass is pushed so that squeezing prod is provided, in the temperature range of 316-455 ℃ (600 ° to 850 ) and with the speed that enough 80% of described squeezing prod is maintained non-recrystallize state at least, carry out this extruding.This squeezing prod is carried out solution heat treatment and artificial aging so that improve strength property and the squeezing prod with improved fracture toughness is provided.
Than the 7xxx product of similar size, the aluminum base alloy extrusion of this improvement can have big at least 8% fracture toughness property and big at least 3% yield strength.
The present invention also comprises the wrought product of the aluminum base alloy of improvement, the squeezing prod of forming by following ingredients basically for example: 1.95 to 2.5% weight Cu, 1.9 to 2.5% weight Mg, 8.2 to 10% weight Zn, 0.05 to 0.25% weight Zr, 0.05 to 0.2% weight Sc, 0.15% weight Si at the most, 0.15% weight Fe at the most, 0.1% weight Mn at the most, the aluminium of surplus and incidental element and impurity.
The accompanying drawing summary
Fig. 1 is the schema that shows step of the present invention.
Fig. 2 illustrates with high strength 7xxx alloy (SSLLC) correlated, the destruction tolerance limit of alloy of the present invention (M703) (normalized depression speed) result.
With reference to Fig. 1, shown the flow chart of the step among the present invention. Usually, with controlled freezing rate the melt of Al-Zn-Mg-Cu alloy is cast in order to obtain specific grain size range in the body of casting in this step. Under controlled condition this body of casting carried out homogenising in order to obtain MgZn thereafter,2Or the sedimentary even distribution of η. This body of casting is pushed in order to obtain for example at least 80% extruded product as non-recrystallization state of its major part take specific speed range and temperature. Then this extruded product is carried out solution heat treatment and timeliness extremely high-caliber intensity, fracture toughness and corrosion resistance.
Alloy of the present invention comprises the Zn of about 8.2 to 10% weight, 1.9 the Mg to 2.5% weight, 1.95 the Cu to 2.5% weight, 0.05 the Zr to 0.25% weight, the Si of 0.15% weight at the most, the Fe of 0.15% weight at the most, the Mn of 0.1% weight at the most, the aluminium of surplus and subsidiary element and impurity.
Preferably, this alloy comprises the Cu of 1.95 to 2.3% weight, the Mg of 1.9 to 2.3% weight, the Zn of 8.45 to 9.4% weight, the Cr of 0.05 to 0.2% weight, the Zr of 0.05 to 0.15% weight. The scope of Cr can be 0.05 to 0.08% weight. In order to delay recrystallization, this alloy can comprise the Sc of 0.01 to 0.2% weight, preferred 0.01 to 0.1% weight. When processing according to the present invention, these alloys and traditional 7xxx alloy for example AA7075-T6 are compared, can accept or even high-caliber intensity and corrosion resistance under have the fracture toughness that significantly improves. The exercise question of publishing in December, 1993 has been set forth the composition of AA7xxx alloy for ABAL's publication of " but the ABAL's name and the chemical composition range that are used for wrought aluminium and Aluminium wrought alloy are registered ". Term " 7xxx " refers to comprise zinc as the aluminium alloy of main alloy compositions. AA7075-T6 refers to the AA compositing range of ABAL's registration. Typical T6 timeliness operation for 7075 is about 121 ℃ (250 ) lower heating 24 hours and heated 3 to 30 hours under the representative temperature scope of about 79-166 ℃ (175 ° to 330 ).
For the present invention, with the speed that controlled microscopic structure or crystallite dimension can be provided molten aluminium alloy of the present invention is cast as solidifying body. When extruded product is made in hope, the form that the typical case casts base bar (billet) with this molten aluminium alloy. In addition, the typical case preferably cast this solidifying body with the speed of 5-10cm (2 to 4 inches) per minute, and this base bar typical case has the diameter of 2.5-18cm (about 1 to 7 inch) scope with about 2.5-15cm (1 to 6 inch) per minute. For the present invention, this solidifying body preferably has 25 to 100 μ m, the average grain size of preferred 35 to 75 μ m. If alloy of the present invention is cast and carried out the heat engine tool according to the present invention and process with the speed of control, can obtain very high stretching and compressive strength, fracture toughness and corrosion resistance. That is, for the expectation microscopic structure that obtains to process for carry out the heat engine tool according to the present invention, with controlled freezing rate molten aluminum is cast. It is found that the combination that the controlled freezing speed of disclosure aluminium alloy and controlled heat engine tool are subsequently processed can produce has the excellent properties extruded product, i.e. very high hot strength, good corrosion and shock-resistant (dent resistance) property.
It should be noted that the intensity that can improve by dispersion hardening or strain hardening aluminium alloy of the present invention. Strain hardening is the result of plastic deformation and the degree that depends on distortion. Dispersion hardening produces by forming cluster (being called Guiner-Preston or GP district). In addition, dispersion hardening also can be by cenotype in the alloy or sedimentary formation and produces, and this cenotype or sediment have formed the obstacle that dislocation moves. This can significantly improve the intensity of alloy. In the Al-Zn-Mg-Cu alloy, new hardening constituent comprises MgZn2, be also referred to as M or η-phase, Mg3Zn
3Al
2Be also referred to as the T-phase, CuMgAl2Be also referred to as the S-phase. The reinforcement that the cenotype precipitation produces is more effective than the reinforcement that forms the generation of GP district. Yet the reinforcement meeting that the cenotype precipitation causes causes adverse effect to destroying tolerance limit or fracture toughness. Usually, the volume fraction of precipitated phase is larger, and destroying tolerance limit can be lower. By contrast, the reinforcement of the formation in GP district generation can not sacrificed and be destroyed the tolerance limit energy. Therefore, for intensity that improvement is provided with destroy tolerance limit, balance of the present invention the volume fraction of sediment volume fraction in the final products and GP district or rich zinc bunch, keep simultaneously the zinc of excessive dissolving. For the present invention, the scope of GP district size should be 2 to 35nm and the scope of GP district density should be every cm34×10
18To 5 * 1018Individual district.
In order to make according to base bar of the present invention, can be with casting by the mould of air and liquid coolant cooling, in order to the base bar is solidified. This crystal grain can have the size of 35 to 75 mu m ranges. The air that together uses with mould and the mixture of cooling agent are particularly suitable for absorbing heat from the aluminium alloy molten mass, thereby can obtain 5 to 50 ℃ freezing rate each second for the base bar with 2.5-15cm (1 to 6 inch) diameter. At United States Patent (USP) 4,598, the mould that uses air and coolant mixture has been described in 763, this mould is suitable for controlling the cooldown rate of casting molten aluminium alloy of the present invention. With being formed by gas and liquid as being used for the cooling agent that these moulds of the present invention use, wherein with gas as small, discrete insoluble bubble injects this liquid and combination on the new ingot bar that forms. Should subsidiary alveolate cooling agent can be with the heat abstraction speed cool metal that improves, and if necessary, can utilize the heat abstraction speed of this raising to control the cooldown rate that any stage of casting operation comprises the stable state cast sections with the cooling agent discharge rate.
In order to cast for example metal of aluminium alloy, in order to the microscopic structure that is suitable for purposes of the present invention is provided, motlten metal is introduced the cavity of this mould by the opening of ring mould one end, and when dividing at mould inside, this metal solidifies and when the supporter adjacent with this cavity other end opening formed the metal freezing body, it was vertically mutually mobile so that with the rear opening extraction of metal freezing body from cavity to make this mould and supporter prolong cavity. Introduce liquid coolant in the annularly flow pipeline around the cavity of mold, this pipeline leads to the adjacent ambient air of the aforementioned end opposite opening of mould, so that with cooling agent curtain discharging cooling agent and impact on the metallic object that is just forming so that directly cooling. Simultaneously, the gas pressurized that substantially is insoluble to this coolant liquid is injected near the annular distributor chamber the pipeline place this mold, this distributor chamber passes into this pipeline by the narrow annular channel that is arranged in this tubes rows outlet upstream and be positioned at around the coolant flow wherein. Gas in cavity part is discharged in this pipeline by this slit, and when by this slit exhaust, is divided into a plurality of gas injection streams by this slit. With uniform temperature and pressure this injection stream is injected coolant flow, under this condition, gas brought into and form a large amount of bubbles in the coolant flow, when the cooling agent curtain was discharged by the opening of pipeline and impacted on the metallic object that is just producing, this bubble tended to keep discrete and insoluble state in cooling agent. The a large amount of bubbles that wherein comprise have been arranged, and this cooling curtain has the speed of raising, and can improve to adjust with this cooldown rate of coolant liquid, because any minimizing of its adequate remedy cooling agent thermal conductivity. In fact, this high speed and the cooling agent curtain that carries bubble may produce the effect of scrubbing to metal, this can destroy any film and reduce the tendency of the film of metal surface generation, thereby (if necessary) allows to carry out this processing under the nuclear of better level is choked fire. The adding of bubble can also produce more cooling agent steam in the cooling agent curtain, the steam of increase tends to rise and enters in the metallic object and the gap between the mold wall that has usually just formed above curtain, and cools off the metal of this position. As a result, metal tends to occur unexpectedly to solidify sooner at wall, and this is not only the result who reaches in the above described manner higher cooldown rate, but also is the result who forms the cooling agent steam in the gap. This higher level can guarantee that metal solidifies with certain level existing on the mold wall of lubricating oil, and simultaneously, all these effects can produce in the whole length of ingot casting excellent, have more satin light shape, without drawing the metal body surface of trace and being particularly suitable for thermal deformation.
When in conjunction with United States Patent (USP) 4,598, when the equipment of describing in 763 and this cooling agent of utilization, this casting method has additional advantage, the any gas and/or the steam that namely are discharged in the gap by curtain can mix with the anchor ring of the fluid of discharging from mold cavity, thereby produce more stable discharge stream, rather than the discharging that occurs as the intermittent pulse of fluid.
As indicated, this gas should have low solvability in this liquid, and when this liquid is water, for cheap and be convenient to utilize for the purpose of this gas can be air.
In casting operation, can be during ingot blank (butt) formation stage and stable state cast sections, by slit with the gas release in the distribution chamber in the coolant flowing pipeline.Perhaps, can just during the stable state cast sections, release the gas in the pipeline by this slit.For example, form the stage at ingot blank, can regulate the drainage rate of refrigerant so that make ingot casting cold excessively by producing the film fiery effect of choking, and need to improve rate of cooling so that during the level of the surface temperature of on metal, keeping expectation when metal temperature reaches, can release the gas in the pipeline by this slit.At this moment, when surface temperature is reduced to aforementioned levels when following, can no longer release the gas in this pipeline, so that make metal cold excessively again by slit.Finally, when stable state when beginning casting, release the gas in the pipeline again by slit and in uncertain mode and to finish up to casting operation.Perhaps, can the ingot blank formation stage regulate refrigerant drainage rate in case with the temperature maintenance of metal within aforesaid scope, and when improving cryogen discharge speed and stable state casting beginning, just release the gas in the pipeline by slit.
United States Patent (USP) 4,598, to refrigerant, mould and castmethod have been carried out further description, quote as a reference here in 763 and 4,693,298.
Though the present invention being made the casting program of base bar is described in detail, wherein this base bar has and is used for according to the required tissue of thermal distortion of the present invention, yet should understand and can use other castmethod that the solidification rate that can produce crystalline-granular texture essential to the invention is provided.As previously described, can cast by belt, monoblock casting or roll-type casting and electromagnetic casting obtain such solidifying.
Contain 8.9% weight Zn, 2.1% weight Mg, 2.3% weight Cu, 0.11% weight Zr, seven inches base bars of the aluminiferous alloy of surplus, use utilizes the casting of the rate of cooling of the mould of air and water coolant and per second 1.7-10 ℃ (35 ° to 50 ), for providing satisfied grain structure according to extruding of the present invention and hot mechanical treatment.
Though about the base bar casting is described, should understands principle described here to be applied to the casting of ingot casting or aluminium alloy electromagnetic.
After the casting base bar, it is carried out homogenizing handle.Preferably, this base bar being carried out twice homogenizing handles.During first homogenizing is handled, preferably in the temperature range of 449-460 ℃ (840 ° to 880 ), the base bar was handled 6 to 18 hours.Preferably the temperature range of 471-482 ℃ (880 ° to 900 s) in base bar handled 4 to 36 hour thereafter.The base bar is carried out above-mentioned dual homogenizing processing MgZn can be provided
2Throw out or M or η phase and the more equally distributed base bar that contains the dispersoid of zinc and chromium.
Homogenizing is pushed so that squeezing prod is provided the base bar after handling.In order to push, the base bar is heated to the temperature of 316-455 ℃ of (600 ° to 850 ) scope and during pushing, the base bar is maintained in this temperature range.Preferably, with 0.8 to 8ft/min speed and preferably the base bar is pushed with the extrusion ratio of 10 to 60 scopes.At least 80% and preferred 90% squeezing prod is the squeezing prod of non-recrystallize state in order to obtain wherein, and these conditions are important.This squeezing prod can have 1: 4 to 1: 18 aspect ratio between thin and the thickest cross section.
After the extruding, product is carried out solution heat treatment by temperature range internal heating at about 452-482 ℃ (845 are to about 900 ), and the temperature range of preferred 466-477 ℃ (870 ° to 890 ).Typical time range under these temperature is 5 to 120 minutes.Should make this solution heat treatment carry out time enough so that dissolve most of alloying element.That is, make whole zinc basically, magnesium and copper dissolution are so that provide sosoloid.
After the solution heat treatment, squeezing prod is cooled off fast or for example spray it is quenched by immersion cold water or with cold water.After the quenching, can align and/or stretch squeezing prod.That is, before timeliness, squeezing prod is aligned so that improve strength property.
After the solution heat treatment, this squeezing prod is handled so that improve for example intensity the performance of corrosion and fracture toughness property.
Therefore, can performance as required carry out different thermal treatment to squeezing prod.For example, can be called the one step thermal treatment of T6 type tempered so that obtain the intensity of height or peak value to squeezing prod.Yet this tempering may be subjected to the influence of stress corrosion crack easily.Can obtain the T6 tempering in 3 to 30 hours by timeliness in the temperature range of 79.4-163 ℃ (175 ° to 325 ).Can use two step ageing treatment, wherein under 79.4-149 ℃ (175 ° to 300 ), carry out first timeliness step and continue for some time of 3 to 30 hours, under 149-182 ℃ (300 ° to 360 ), carry out second timeliness step subsequently and continue for some time of 3 to 24 hours.This ageing treatment can produce and be called as T7x tempered overaging tempering.This state can improve the stress corrosion crack performance but can reduce intensity.
In order to improve intensity and erosion resistance, can carry out three step aging techniques to squeezing prod.This timeliness step or stage comprise low-Gao-low timeliness operation.In first or low timeliness step, squeezing prod is applied certain temperature and continues for some time, throw out can be strengthened this squeezing prod and reach or near peak strength therebetween.This can realize by carry out precipitation hardening and typical lasting 2 to 30 hours time in the temperature range of about 66-163 ℃ (150 ° to 325 ).Then, squeezing prod being carried out second handles so that improve erosion resistance.Second processing is included in the temperature range interior processing squeezing prod of 149-260 ℃ (300 ° to 500 ) and continues for example 5 minutes to about 3 hours.In the 3rd step, squeezing prod is carried out another strengthen step.The 3rd thermal treatment is included under the temperature of 79.4-163 ℃ (175 ° to 325 ) squeezing prod was handled about 2 to 30 hours.
Exfoliation corrosion (EXCO) characteristic of alloy of the present invention and 7075 T6511 and 7075T76511 alloy are compared.American Society Testing and Materials develops the method for the acceleration exfoliation corrosion test that can be provided for 2xxx and 7xxx series alloys.The performance rate that uses the reference standard photo to set up is determined the susceptibility peeled off by estimating.When testing according to this test method, when timeliness during to the T76 tempering, alloy of the present invention can show typical EA exfoliation corrosion grade.When timeliness during to the T77 tempering, alloy of the present invention can show typical EB exfoliation corrosion grade.
Though about squeezing prod alloy is described, expects that herein this alloy also can be used as thin plate or slab product.
Here the four corner of Ti Chuing comprises all numerical value in the scope, as specifically describing.
Described here be specially adapted to aerospace application and can be at large aircraft obtain many application in for example commercial and military aircraft according to product of the present invention or parts.This product can be used for the wing member, tail assemblies, other assembly of fuselage part or assembly or formation aircraft.That is, this aircraft components can comprise airfoil member or wing components, wing centre section box part or assembly, and floor component or assembly comprise seat guide rail, floor bearer, pillar, cargo loading plate parts and assembly, floor panel, cargo floor panels, body parts or assembly fuselage ring, body longeron etc.In addition, can make this product and be used for for example bat of sports goods with the form of seamless or non-seamless tubular goods.
Form
For the thick squeezing prod of 0.63cm (0.249 inch), the comparison of the typical machine performance of alloy of the present invention (M703) and 7075 T6511 and 7150 T77511.
| Alloy | Tempering | UTS，MPa(ksi) | YS，MPa(ksi) | e y％ | K Ic |
| 7075 | T6511 | 607(88) | 565(82) | 10 | 28 |
| M703 | T76511 | 669(97) | 641(93) | 10 | 33 |
| M703 | T77511 | 703(102) | 689(100) | 9 | 32.5 |
| 7150 | T77511 | 641(93) | 614(89) | 9 | 27 |
This explanation of tables when the mechanical property of timeliness alloy of the present invention during to T76 and T77 tempering.
The following example carries out further exemplary illustration to the present invention.
To comprise 8.9% weight Zn, 2.1% weight Mg, 2.3% weight Cu, 0.11% weight Zr, subsidiary element and impurity, the alloy preform bar of surplus aluminium is cast the base bar of 7 inches of diameters.Use utilizes the mold of air and liquid coolant, and (available from Wagstaff Engineering Inc., Spokane Washington) casts this base bar.Regulate this air/water refrigerant, so that cast the molten mass of this aluminium alloy with the speed of 4 inches of per minutes.Tissue after this casting has the average grain size of 35 μ m.Keep down keeping down this base bar being carried out homogenizing in 24 hours at 477 ℃ (890 ) then in 8 hours at 466 ℃ (870 ).Thereafter, make the base bar be in 385 ℃ (725 ) and be squeezed into hollow tube then, this tubing has the external diameter of 6.7cm (2.65 inches) and the wall thickness of 0.2cm (0.080 inch).
This squeezing prod has non-recrystal grain tissue.The solution heat treatment under 471 ℃ (880 ) of this squeezing prod was quenched in water-15% ethylene glycol solution in 25 minutes then.Thereafter, under 121 ℃ (250 ) this quenching squeezing prod is carried out precipitation hardening and continues 24 hours then, the temperature that is placed on 157 ℃ (315 ) also continued 6 hours so that improve erosion resistance and yield strength performance.Then this squeezing prod is carried out the test of tensile strength and yield strength and compare with AA 7075 T6.The result is as shown in table 1.
Carry out shock-resistant to this squeezing prod then or the test of destruction tolerance limit.Carry out impulse withstand test by ball from weight to extruded tube that throw same size and.The throwing number that forms first indenture on extruded tube is represented shock-resistance.This squeezing prod and the AA7055 alloy of handling are in a similar manner compared.Alloy of the present invention is called M703 and is called SSLLC (referring to Fig. 2) with 7055.Two kinds of alloys are carried out same timeliness.As can be seen from Figure 2 M703 has more excellent in impact resistance.
Embodiment 2
To comprise 8.9% weight Zn, 2.1% weight Mg, 2.3% weight Cu, 0.11% weight Zr, subsidiary element and impurity, the alloy preform bar of surplus aluminium is cast the base bar of diameter 18cm (7 inches).Use utilizes the mold of air and liquid coolant, and (available from Wagstaff Engineering Inc., Spokane Washington) casts this base bar.Regulate this air/water refrigerant so that cast the molten mass of this aluminium alloy with the speed of 4 inches of per minutes.Tissue after this casting has the average grain size of 35 μ m.Keep down keeping down this base bar being carried out homogenizing in 24 hours at 477 ℃ (890 ) then in 8 hours at 466 ℃ (870 ).Make base bar be in aircraft longeron that 385 ℃ (725 s) then be squeezed into wall thickness with T type cross section and 0.62cm (0.245 inch) thereafter.
This squeezing prod has non-recrystal grain tissue.The solution heat treatment under 471 ℃ (880 ) of this squeezing prod was quenched in water-15% ethylene glycol solution in 35 minutes then., 121 ℃ (250 s) under this quenching squeezing prod carried out precipitation hardening and continue 24 hour subsequently at 193 ℃ (380 s) down keep 25 to 35 minute, kept 24 hours down at 121 ℃ (250 ) then thereafter.Then this squeezing prod is carried out tensile strength and yield strength and fracture toughness property, the test of fatigue crack growth also compares with AA 7075 T6511 and AA7150 T77511.The result is as shown in table 1.When comparing with AA 7075 T6511 and AA7150 T77511, alloy of the present invention has more excellent intensity and fracture toughness property as can be seen.In addition, this squeezing prod has unique tensile strength, the combination of erosion resistance and destruction tolerance limit (being fracture toughness property and fatigue crack growth).
The preferred embodiments of the invention are described, should understand within the scope of the appended claims and can implement the present invention in other mode.
Claims (29)
1. make the method for the aluminium alloy extruded product with improved fracture toughness, this method comprises the following steps:
(a) provide by 1.95 to 2.5% weight Cu, greater than 1.9 to 2.5% weight Mg, 8.2 to 10% weight Zn, 0.05 to 0.25% weight Zr, 0.15% weight Si at the most, 0.15% weight Fe at the most, 0.1% weight Mn at the most, the molten mass of the aluminum base alloy that the aluminium of surplus and subsidiary element and impurity are formed;
(b) the described molten mass of described aluminum base alloy is cast so that congealed solid is provided, cast described molten aluminum matrix alloy with the speed of per minute 2.5-15cm;
(c) by at 460-471 ℃ the second temperature range internal heating described congealed solid being carried out homogenizing subsequently at 449-460 ℃ the first temperature range internal heating, and second homogenization temperature is greater than first homogenization temperature, so that the equally distributed homogeneous mass that has the η throw out and contain the zirconium dispersion is provided;
(d) described homogeneous mass is pushed so that squeezing prod is provided, in 316-455 ℃ temperature range and at least 80% speed that maintains non-recrystallize state that is enough to the cross-sectional area of described squeezing prod, carry out described extruding;
(e) described squeezing prod is carried out solution heat treatment; With
(f) described product is carried out artificial aging so that improve strength property, thereby yield strength with improvement squeezing prod with the fracture toughness property ratio is provided.
2. according to the process of claim 1 wherein that this alloy comprises 1.95 to 2.3% weight Cu.
3. according to the process of claim 1 wherein that this alloy comprises greater than 1.9 to 2.3% weight Mg.
4. according to the process of claim 1 wherein that this alloy comprises 0.05 to 0.2% weight Cr.
5. according to the process of claim 1 wherein that this alloy comprises 8.45 to 9.4% weight Zn.
6. according to the process of claim 1 wherein that this alloy comprises 0.01 to 0.1% weight Sc.
7. according to the process of claim 1 wherein that this alloy comprises 0.01 to 0.2% weight Ti.
8. according to the method for claim 1, this method was included in the described first temperature range internal heating 6 to 18 hours.
9. according to the method for claim 1, this method was included in the described second temperature range internal heating 4 to 36 hours.
10. according to the method for claim 1, this method comprises carries out rapid quenching to described squeezing prod.
11. according to the process of claim 1 wherein that the speed with 0.15-2.4m/min carries out described extruding.
12. in 466-477 ℃ temperature range, carry out described solution heat treatment and continue 5 to 120 minutes according to the process of claim 1 wherein.
13. carried out described artificial aging in 3 to 24 hours 138-182 ℃ of following timeliness subsequently in 3 to 30 hours by timeliness in 79.4-149 ℃ temperature range according to the process of claim 1 wherein.
14. carried out described artificial aging in 30 minutes to 14 hours 160-204 ℃ of following timeliness subsequently in 4 to 24 hours by timeliness in 99-138 ℃ temperature range according to the process of claim 1 wherein.
15. carried out described artificial aging in 2 to 30 hours 79.4-163 ℃ of following timeliness subsequently in 5 minutes to 3 hours 149-260 ℃ of following timeliness subsequently in 2 to 30 hours by timeliness in 66-163 ℃ temperature range according to the process of claim 1 wherein.
16. according to the process of claim 1 wherein that described artificial aging is a three step process, the wherein said the first step and the 3rd step are improved intensity and second step raising erosion resistance.
17. according to the process of claim 1 wherein that described artificial aging comprises: (i) be higher than timeliness under the low temperature of room temperature so that described squeezing prod is carried out precipitation hardening; (ii) timeliness under the temperature of the corrosion resistance that improves described squeezing prod; (iii) be higher than timeliness under the lesser temps of room temperature so that described squeezing prod is carried out precipitation hardening.
18. according to the process of claim 1 wherein that this squeezing prod has the fracture toughness property than the similar squeezing prod of being made by 7075 alloys big at least 5%.
19. according to the process of claim 1 wherein that this squeezing prod has the tensile strength than the similar squeezing prod of being made by 7075 alloys big at least 8%.
20. make the method for the aluminium alloy extruded product with improved strength and fracture toughness property, this method comprises the following steps:
(a) provide by 1.95 to 2.3% weight Cu, greater than 1.9 to 2.3% weight Mg, 8.2 to 9.4% weight Zn, 0.05 to 0.2% weight Cr, 0.05 to 0.15% weight Zr, 0.15% weight Si, 0.15% weight Fe at the most at the most, 0.1% weight Mn at the most, the molten mass of the aluminum base alloy that the aluminium of surplus and subsidiary element and impurity are formed;
(b) the described molten mass of described aluminum base alloy is cast so that congealed solid is provided, cast described molten aluminum matrix alloy with the speed of per minute 2.5-15cm;
(c) by described congealed solid being carried out homogenizing in 4 to 36 hours at 460-471 ℃ the second temperature range internal heating subsequently 449-460 ℃ the first temperature range internal heating 6 to 24 hours, and second homogenization temperature is greater than first homogenization temperature, so that the equally distributed homogeneous mass that has the η throw out and contain the dispersion of zirconium and chromium is provided;
(d) described homogeneous mass is pushed so that squeezing prod is provided, in 316-455 ℃ temperature range and with the speed of 0.15-2.4m/min, carry out described extruding so that provide non-recrystallize zone to account for the squeezing prod of this squeezing prod cross section at least 80%;
(e) described squeezing prod is carried out rapid quenching;
(f) described squeezing prod is carried out solution heat treatment; With
(g) described product is carried out artificial aging so that improve strength property, thereby yield strength with improvement squeezing prod with the fracture toughness property ratio is provided.
21. make the method for the aluminium alloy extruded product with improved strength and fracture toughness property, this method comprises the following steps:
(a) provide by 1.95 to 2.5% weight Cu, greater than 1.9 to 2.5% weight Mg, 8.2 to 10% weight Zn, 0.05 to 0.25% weight Zr, 0.15% weight Si at the most, 0.15% weight Fe at the most, 0.1% weight Mn at the most, the molten mass of the aluminum base alloy that the aluminium of surplus and subsidiary element and impurity are formed;
(b) the described molten mass of described aluminum base alloy is cast so that congealed solid is provided, cast described molten aluminum matrix alloy with the speed of per minute 2.5-10cm;
(c) described congealed solid is carried out homogenizing and have the sedimentary equally distributed homogeneous mass of η so that provide;
(d) described homogeneous mass is pushed so that squeezing prod is provided, in 316-455 ℃ temperature range and with 10 to 60 extrusion ratio and the extruding rate of 0.15-2.4m/min, carry out described extruding, so that the squeezing prod that is in non-basically recrystallize state is provided;
(e) described squeezing prod is carried out rapid quenching;
(f) described squeezing prod is carried out solution heat treatment; With
(g) described product is carried out artificial aging so that improve strength property, thereby yield strength with improvement squeezing prod with the fracture toughness property ratio is provided.
22. the wrought product of improvement aluminum base alloy, it is basically by 1.95 to 2.5% weight Cu, greater than 1.9 to 2.5% weight Mg, 8.2 to 10% weight Zn, 0.05 to 0.25% weight Zr, 0.15% weight Si at the most, 0.15% weight Fe at the most, 0.1% weight Mn at the most, the aluminium of surplus and subsidiary element and impurity are formed, and described alloy product has than the fracture toughness property of 7075 products big 5% of similar size and big 8% yield strength at least at least.
23. according to the alloy product of claim 22, wherein said product is the aircraft longeron.
24. according to the alloy product of claim 22, wherein said product is the aircraft floor bearer.
25. according to the alloy product of claim 22, wherein said product is the airframe beam.
26. the wrought product of improvement aluminum base alloy, it is basically by 1.95 to 2.5% weight Cu, greater than 1.9 to 2.5% weight Mg, 8.2 to 10% weight Zn, 0.05 to 0.25% weight Zr, 0.05 to 0.2% weight Sc, 0.15% weight Si at the most, 0.15% weight Fe at the most, 0.1% weight Mn at the most, the aluminium of surplus and subsidiary element and impurity are formed.
27. the wrought product of improvement aluminum base alloy, it is basically by 1.95 to 2.5% weight Cu, greater than 1.9 to 2.5% weight Mg, 8.2 to 10% weight Zn, 0.05 to 0.25% weight Zr, 0.15% weight Si at the most, 0.15% weight Fe at the most, 0.1% weight Mn at the most, the aluminium of surplus and subsidiary element and impurity are formed, and described alloy product has than the yield strength of the fracture toughness property of 7075 products big at least 5% of similar size and big at least 8% and has EB or better stripper-resistance.
28. the aircraft components of improvement aluminum base alloy, it is basically by 1.95 to 2.5% weight Cu, greater than 1.9 to 2.5% weight Mg, 8.2 to 10% weight Zn, 0.05 to 0.25% weight Zr, 0.15% weight Si at the most, 0.15% weight Fe at the most, 0.1% weight Mn at the most, the aluminium of surplus and subsidiary element and impurity are formed, and described alloy product has than the fracture toughness property of 7075 products big 5% of similar size and big 8% yield strength at least at least.
29. the aircraft components of improvement aluminum base alloy, it is basically by 1.95 to 2.5% weight Cu, greater than 1.9 to 2.5% weight Mg, 8.2 to 10% weight Zn, 0.05 to 0.25% weight Zr, 0.15% weight Si at the most, 0.15% weight Fe at the most, 0.1% weight Mn at the most, the aluminium of surplus and subsidiary element and impurity are formed, described alloy product has than the fracture toughness property of 7075 products big 5% of similar size and big 8% yield strength at least at least, and has EB or better stripper-resistance.
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| EP (1) | EP1543174B1 (en) |
| JP (1) | JP2006504871A (en) |
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| US1418303A (en) * | 1921-02-18 | 1922-06-06 | Rolls Royce | Aluminum alloy |
| US2290020A (en) * | 1941-08-07 | 1942-07-14 | Nat Smelting Co | Aluminum alloy |
| US3637441A (en) * | 1968-04-08 | 1972-01-25 | Aluminum Co Of America | Aluminum-copper-magnesium-zinc powder metallurgy alloys |
| US3563814A (en) * | 1968-04-08 | 1971-02-16 | Aluminum Co Of America | Corrosion-resistant aluminum-copper-magnesium-zinc powder metallurgy alloys |
| US4711762A (en) * | 1982-09-22 | 1987-12-08 | Aluminum Company Of America | Aluminum base alloys of the A1-Cu-Mg-Zn type |
| JPS6013047A (en) * | 1983-06-30 | 1985-01-23 | Showa Alum Corp | High-strength aluminum alloy with superior cold workability |
| US4732610A (en) * | 1986-02-24 | 1988-03-22 | Aluminum Company Of America | Al-Zn-Mg-Cu powder metallurgy alloy |
| US5221377A (en) * | 1987-09-21 | 1993-06-22 | Aluminum Company Of America | Aluminum alloy product having improved combinations of properties |
| CA1340618C (en) * | 1989-01-13 | 1999-06-29 | James T. Staley | Aluminum alloy product having improved combinations of strength, toughness and corrosion resistance |
| JPH036345A (en) * | 1989-06-02 | 1991-01-11 | Daido Metal Co Ltd | Aluminum-base alloy for sliding use excellent in fatigue resistance and seizure resistance |
| US5312498A (en) * | 1992-08-13 | 1994-05-17 | Reynolds Metals Company | Method of producing an aluminum-zinc-magnesium-copper alloy having improved exfoliation resistance and fracture toughness |
| EP0694084B1 (en) * | 1993-04-15 | 2001-09-19 | Luxfer Group Limited | Method of making hollow bodies |
| US5496426A (en) * | 1994-07-20 | 1996-03-05 | Aluminum Company Of America | Aluminum alloy product having good combinations of mechanical and corrosion resistance properties and formability and process for producing such product |
| JPH08295977A (en) * | 1995-04-21 | 1996-11-12 | Sumitomo Light Metal Ind Ltd | High strength aluminum alloy extruded material excellent in fatigue strength and motorcycle front fork outer tube material |
| US6315842B1 (en) * | 1997-07-21 | 2001-11-13 | Pechiney Rhenalu | Thick alznmgcu alloy products with improved properties |
| JP4229307B2 (en) * | 1998-11-20 | 2009-02-25 | 住友軽金属工業株式会社 | Aluminum alloy plate for aircraft stringers having excellent stress corrosion cracking resistance and method for producing the same |
| WO2005003398A2 (en) * | 2003-04-23 | 2005-01-13 | Kaiser Aluminum & Chemical Corporation | High strength aluminum alloys and process for making the same |
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2003
- 2003-09-15 US US10/662,835 patent/US20040099352A1/en not_active Abandoned
- 2003-09-19 CA CA2499542A patent/CA2499542C/en not_active Expired - Fee Related
- 2003-09-19 BR BR0314845-9A patent/BR0314845A/en not_active Application Discontinuation
- 2003-09-19 JP JP2004553427A patent/JP2006504871A/en active Pending
- 2003-09-19 CN CNB038244020A patent/CN100339501C/en not_active Expired - Fee Related
- 2003-09-19 AU AU2003302139A patent/AU2003302139A1/en not_active Abandoned
- 2003-09-19 EP EP03808403A patent/EP1543174B1/en not_active Revoked
- 2003-09-19 WO PCT/US2003/029671 patent/WO2004046402A2/en active Application Filing
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020121319A1 (en) * | 2000-12-21 | 2002-09-05 | Chakrabarti Dhruba J. | Aluminum alloy products having improved property combinations and method for artificially aging same |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101967614A (en) * | 2010-11-24 | 2011-02-09 | 中国兵器工业第五九研究所 | Homogenizing treatment method for strengthening Al-Zn-Mg-Cu series ultrahigh strength aluminum alloy |
Also Published As
| Publication number | Publication date |
|---|---|
| EP1543174A2 (en) | 2005-06-22 |
| AU2003302139A1 (en) | 2004-06-15 |
| AU2003302139A8 (en) | 2004-06-15 |
| EP1543174B1 (en) | 2010-09-15 |
| US20040099352A1 (en) | 2004-05-27 |
| WO2004046402A3 (en) | 2004-08-26 |
| EP1543174A4 (en) | 2005-10-05 |
| CA2499542C (en) | 2011-08-23 |
| CA2499542A1 (en) | 2004-06-03 |
| BR0314845A (en) | 2005-08-09 |
| JP2006504871A (en) | 2006-02-09 |
| WO2004046402A2 (en) | 2004-06-03 |
| CN1692174A (en) | 2005-11-02 |
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